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\n  \n 2025\n \n \n (10)\n \n \n
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\n \n\n \n \n White, A.; and Hanquist, K. M.\n\n\n \n \n \n \n Formulation of an Uncertainty Analysis Methodology for Computational Fluid Dynamics of External Flows Over Launch Vehicles.\n \n \n \n\n\n \n\n\n\n In AIAA AVIATION FORUM AND ASCEND 2025, 2025. AIAA Paper 2025-3409\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{white2025,\n\ttitle = {Formulation of an {Uncertainty} {Analysis} {Methodology} for {Computational} {Fluid} {Dynamics} of {External} {Flows} {Over} {Launch} {Vehicles}},\n\tdoi = {10.2514/6.2025-3409},\n\tabstract = {Space launch vehicles are often engineered with large safety factors due to the scarcity and cost of ground tests. In addition, these vehicles often carry expensive and delicate payloads that must go through extreme launch conditions. Computational Fluid Dynamics (CFD) can be utilized to support the design of these vehicles but often have uncertainty and errors associated with them that are often not fully quantified. This paper provides a methodology and investigation for quantifying and estimating the uncertainty for CFD over space launch vehicles when no experimental data exists. A generic launch vehicle was used for this study. The primary output quantities of interest for the study are the aerodynamic coefficients. While there are numerous sources of uncertainty, this study investigates the impact of mesh quality, boundary conditions, and turbulence models. The largest uncertainty lies in the y-moment coefficient, where the y-axis is aligned with the angle of attack, and is due to perturbing the turbulence model for a zero-degree angle of attack configuration or perturbing the mesh quality for a six-degree angle of attack configuration. The smallest uncertainty is in the x-moment coefficient, with a zero percent uncertainty for all configurations.},\n\turldate = {2025-09-09},\n\tbooktitle = {{AIAA} {AVIATION} {FORUM} {AND} {ASCEND} 2025},\n\tpublisher = {AIAA Paper 2025-3409},\n\tauthor = {White, Avery and Hanquist, Kyle M.},\n\tyear = {2025},\n}\n\n\n\n
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\n Space launch vehicles are often engineered with large safety factors due to the scarcity and cost of ground tests. In addition, these vehicles often carry expensive and delicate payloads that must go through extreme launch conditions. Computational Fluid Dynamics (CFD) can be utilized to support the design of these vehicles but often have uncertainty and errors associated with them that are often not fully quantified. This paper provides a methodology and investigation for quantifying and estimating the uncertainty for CFD over space launch vehicles when no experimental data exists. A generic launch vehicle was used for this study. The primary output quantities of interest for the study are the aerodynamic coefficients. While there are numerous sources of uncertainty, this study investigates the impact of mesh quality, boundary conditions, and turbulence models. The largest uncertainty lies in the y-moment coefficient, where the y-axis is aligned with the angle of attack, and is due to perturbing the turbulence model for a zero-degree angle of attack configuration or perturbing the mesh quality for a six-degree angle of attack configuration. The smallest uncertainty is in the x-moment coefficient, with a zero percent uncertainty for all configurations.\n
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\n \n\n \n \n Larsen, A.; and Hanquist, K. M.\n\n\n \n \n \n \n Vibrational State-to-State and Shock-Tube Thermochemical Modeling of Hypersonic Flows.\n \n \n \n\n\n \n\n\n\n In AIAA AVIATION FORUM AND ASCEND 2025, 2025. AIAA Paper 2025-3560\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{larsen2025,\n\ttitle = {Vibrational {State}-to-{State} and {Shock}-{Tube} {Thermochemical} {Modeling} of {Hypersonic} {Flows}},\n\tdoi = {10.2514/6.2025-3560},\n\tabstract = {Hypersonic flows give rise to nonequilibrium conditions that require increased precision and more specialized simulations to model the collisions between excited gas molecules. While the rotational energy mode is often in equilibrium with the translation mode, the vibrational mode requires more collisions, and thus more time, to reach equilibrium. In this paper, we investigate four main areas of interest. First, state-resolved rates are often generated on different potential energy surface so we investigate ways to do a consistent mapping from one energy surface to another. Next, vibrational state-to-state modeling is investigated, through analysis of existing data and the implementation into existing hypersonic code. Due to differences in energy levels between existing data, data mapping methods are investigated to ensure uniformity in simulations. Further, nonequilibrium effects for canonical flows are modeled using both one-temperature and two-temperature models. Finally, the modeling of one-dimensional shock flows is investigated to prepare for the introduction of state-to-state models within these shock flows.},\n\turldate = {2025-09-09},\n\tbooktitle = {{AIAA} {AVIATION} {FORUM} {AND} {ASCEND} 2025},\n\tpublisher = {AIAA Paper 2025-3560},\n\tauthor = {Larsen, Aaron and Hanquist, Kyle M.},\n\tyear = {2025},\n}\n\n\n\n
\n
\n\n\n
\n Hypersonic flows give rise to nonequilibrium conditions that require increased precision and more specialized simulations to model the collisions between excited gas molecules. While the rotational energy mode is often in equilibrium with the translation mode, the vibrational mode requires more collisions, and thus more time, to reach equilibrium. In this paper, we investigate four main areas of interest. First, state-resolved rates are often generated on different potential energy surface so we investigate ways to do a consistent mapping from one energy surface to another. Next, vibrational state-to-state modeling is investigated, through analysis of existing data and the implementation into existing hypersonic code. Due to differences in energy levels between existing data, data mapping methods are investigated to ensure uniformity in simulations. Further, nonequilibrium effects for canonical flows are modeled using both one-temperature and two-temperature models. Finally, the modeling of one-dimensional shock flows is investigated to prepare for the introduction of state-to-state models within these shock flows.\n
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\n \n\n \n \n Bemis, B. L.; Peck, M. M.; Hanquist, K. M.; Gordeyev, S.; and Juliano, T.\n\n\n \n \n \n \n Stationary Crossflow and Traveling Instabilities for a Slab Delta in Hypersonic Flow.\n \n \n \n\n\n \n\n\n\n In AIAA AVIATION FORUM AND ASCEND 2025, 2025. AIAA Paper 2025-3536\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{bemis2025,\n\ttitle = {Stationary {Crossflow} and {Traveling} {Instabilities} for a {Slab} {Delta} in {Hypersonic} {Flow}},\n\tdoi = {10.2514/6.2025-3536},\n\tabstract = {Stationary crossflow and traveling instabilities on a ‘slab delta’ model were investigated in a hypersonic flow. Experiments were conducted in the AFOSR–Notre Dame Large Mach-6 Quiet Tunnel at nominally zero angle of attack and yaw at unit Reynolds numbers from 4.1 · 10{\\textasciicircum}6 /m to 12.2 · 10{\\textasciicircum}6 /m. Infrared thermography was employed to measure the surface heat-flux distribution, assess the boundary-layer state, track the paths of the stationary crossflow waves, and quantify the flow uniformity. These measurements visualized characteristic streamwise heating streaks and outboard transition lobes. Linear Stability Theory (LST) calculations using the Linear Parabolized Stability Equation (LPSE) at Re∞ = 11.78 ·10{\\textasciicircum}6 /m predicted the most-amplified waves would have a wavelength of 6 mm, a frequency of 13.75 kHz, and propagate towards the centerline with a wave speed of 81 m/s. Traveling waves were measured using surface-flush Kulite pressure transducer trios. Cross-spectral analysis of the pressure signals yielded wave angles and phase speeds as functions of frequency. Traveling waves were observed at Reynolds numbers ranging from 4.1 · 10{\\textasciicircum}6 /m to 9.8 · 10{\\textasciicircum}6 /m, with peak frequencies centered in the range from 7 to 10 kHz. Within experimental uncertainties, the wave angle and phase were found to be largely invariant with Reynolds number. The variation with frequency of experimentally obtained wave angle and phase speed agreed with LST predictions, but experiments exhibited mild left/right differences and phase-speed discrepancies not predicted by LST.},\n\turldate = {2025-09-09},\n\tbooktitle = {{AIAA} {AVIATION} {FORUM} {AND} {ASCEND} 2025},\n\tpublisher = {AIAA Paper 2025-3536},\n\tauthor = {Bemis, Benjamin L. and Peck, Madeline M. and Hanquist, Kyle M. and Gordeyev, Stanislav and Juliano, Thomas},\n\tyear = {2025},\n}\n\n\n\n\n\n\n\n\n\n\n\n
\n
\n\n\n
\n Stationary crossflow and traveling instabilities on a ‘slab delta’ model were investigated in a hypersonic flow. Experiments were conducted in the AFOSR–Notre Dame Large Mach-6 Quiet Tunnel at nominally zero angle of attack and yaw at unit Reynolds numbers from 4.1 · 10\\textasciicircum6 /m to 12.2 · 10\\textasciicircum6 /m. Infrared thermography was employed to measure the surface heat-flux distribution, assess the boundary-layer state, track the paths of the stationary crossflow waves, and quantify the flow uniformity. These measurements visualized characteristic streamwise heating streaks and outboard transition lobes. Linear Stability Theory (LST) calculations using the Linear Parabolized Stability Equation (LPSE) at Re∞ = 11.78 ·10\\textasciicircum6 /m predicted the most-amplified waves would have a wavelength of 6 mm, a frequency of 13.75 kHz, and propagate towards the centerline with a wave speed of 81 m/s. Traveling waves were measured using surface-flush Kulite pressure transducer trios. Cross-spectral analysis of the pressure signals yielded wave angles and phase speeds as functions of frequency. Traveling waves were observed at Reynolds numbers ranging from 4.1 · 10\\textasciicircum6 /m to 9.8 · 10\\textasciicircum6 /m, with peak frequencies centered in the range from 7 to 10 kHz. Within experimental uncertainties, the wave angle and phase were found to be largely invariant with Reynolds number. The variation with frequency of experimentally obtained wave angle and phase speed agreed with LST predictions, but experiments exhibited mild left/right differences and phase-speed discrepancies not predicted by LST.\n
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\n \n\n \n \n Grover, M. S.; Valentini, P.; Bisek, N. J.; Jo, S. M.; Davuluri, R.; Martin, A.; Notey, A.; Panesi, M.; Andrienko, D.; Hanquist, K. M.; and Fraijo, D.\n\n\n \n \n \n \n Comparative Analysis of Thermophysics Models for the Simulations of Nonequilibrium Flow.\n \n \n \n\n\n \n\n\n\n In AIAA SCITECH 2025 Forum, 2025. AIAA 2025-0641\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{grover_comparative_2025,\n\ttitle = {Comparative {Analysis} of {Thermophysics} {Models} for the {Simulations} of {Nonequilibrium} {Flow}},\n\tabstract = {Advances in computational capabilities have allowed for the calculation of canonical hypersonic flows using the direct molecular simulation method. DMS is a particle method that uses quantum mechanically derived interaction potentials to simulate molecular collisions within a flow field. Since these interaction potentials are the only modeling inputs used in the simulation, all flow features can solely be attributed to the ab initio potential energy surfaces. The fundamental nature of these simulations lends to be used as benchmarks to assess lower fidelity models. In this work we investigated two canonical hypersonic flows, where the dominant gas-phase chemical activity was the dissociation of free stream diatomic species: (a) Mach 21 nitrogen flow over a blunt wedge and (b) Mach 8.2 oxygen flow over a double cone geometry. For the comparative analysis we consider seven actively used CFD codes and five thermochemical models. It is observed that new generation of thermochemistry models based in ab initio provide solutions that are more physical and compare favorably to the first principles DMS.},\n\turldate = {2025-07-09},\n\tbooktitle = {{AIAA} {SCITECH} 2025 {Forum}},\n\tpublisher = {AIAA 2025-0641},\n\tauthor = {Grover, Maninder S. and Valentini, Paolo and Bisek, Nicholas J. and Jo, Sung Min and Davuluri, Raghava and Martin, Alexandre and Notey, Aakanksha and Panesi, Marco and Andrienko, Daniil and Hanquist, Kyle M. and Fraijo, Daniel},\n\tyear = {2025},\n}\n\n\n\n\n\n\n\n
\n
\n\n\n
\n Advances in computational capabilities have allowed for the calculation of canonical hypersonic flows using the direct molecular simulation method. DMS is a particle method that uses quantum mechanically derived interaction potentials to simulate molecular collisions within a flow field. Since these interaction potentials are the only modeling inputs used in the simulation, all flow features can solely be attributed to the ab initio potential energy surfaces. The fundamental nature of these simulations lends to be used as benchmarks to assess lower fidelity models. In this work we investigated two canonical hypersonic flows, where the dominant gas-phase chemical activity was the dissociation of free stream diatomic species: (a) Mach 21 nitrogen flow over a blunt wedge and (b) Mach 8.2 oxygen flow over a double cone geometry. For the comparative analysis we consider seven actively used CFD codes and five thermochemical models. It is observed that new generation of thermochemistry models based in ab initio provide solutions that are more physical and compare favorably to the first principles DMS.\n
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\n \n\n \n \n Xu, B.; Huang, T.; Jing, J.; Zhang, C.; Li, K.; Wang, Y.; and Ye, T.\n\n\n \n \n \n \n \n Heat flux distribution and deviation of stagnation point on blunt body under atmospheric dense environment.\n \n \n \n \n\n\n \n\n\n\n Energy, 319: 135007. March 2025.\n \n\n\n\n
\n\n\n\n \n \n \"HeatPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{xu_heat_2025,\n\ttitle = {Heat flux distribution and deviation of stagnation point on blunt body under atmospheric dense environment},\n\tvolume = {319},\n\tissn = {03605442},\n\turl = {https://linkinghub.elsevier.com/retrieve/pii/S0360544225006498},\n\tdoi = {10.1016/j.energy.2025.135007},\n\tabstract = {Rocket sled is a large ground dynamic test system that obtains model test data on a special ground track. To accurately predict heat flux on rocket sled’s surface, a similar blunt body model is utilized in this study. The effects of flow temperature, Mach number, wall temperature, angle of attack and other parameters on aerodynamic heating at standard atmosphere are analyzed based on computational fluid dynamics (CFD) simulation. The results show that heat flux at stagnation point is 4 MW/m2 at Mach 5. However, maximum heat flux on surface of blunt body head is 13 MW/m2, which deviates 5 mm from stagnation point in horizontal direction. These deviation points are distributed around axis of the cone, forming a band called pseudo-stagnation ring. In two dimensions, bluntness and flight height of cone directly affect position of “pseudo-stagnation point”. This position gradually approaches stagnation point as flight altitude increases. At 30 km altitude, “pseudo-stagnation point” position will not be offset. And at an altitude of 20–30 km, “pseudo-stagnation point” quickly falls back to the stagnation point. Additionally, pseudo-stagnation point’s displacement is inversely related to cone’s bluntness, and an increase in angle of attack augments separation from stagnation point on both windward and leeward surfaces.},\n\tlanguage = {en},\n\turldate = {2025-05-29},\n\tjournal = {Energy},\n\tauthor = {Xu, Bin and Huang, Tianchen and Jing, Jianbin and Zhang, Chuanxia and Li, Kang and Wang, Yangliang and Ye, Taohong},\n\tmonth = mar,\n\tyear = {2025},\n\tpages = {135007},\n}\n\n\n\n
\n
\n\n\n
\n Rocket sled is a large ground dynamic test system that obtains model test data on a special ground track. To accurately predict heat flux on rocket sled’s surface, a similar blunt body model is utilized in this study. The effects of flow temperature, Mach number, wall temperature, angle of attack and other parameters on aerodynamic heating at standard atmosphere are analyzed based on computational fluid dynamics (CFD) simulation. The results show that heat flux at stagnation point is 4 MW/m2 at Mach 5. However, maximum heat flux on surface of blunt body head is 13 MW/m2, which deviates 5 mm from stagnation point in horizontal direction. These deviation points are distributed around axis of the cone, forming a band called pseudo-stagnation ring. In two dimensions, bluntness and flight height of cone directly affect position of “pseudo-stagnation point”. This position gradually approaches stagnation point as flight altitude increases. At 30 km altitude, “pseudo-stagnation point” position will not be offset. And at an altitude of 20–30 km, “pseudo-stagnation point” quickly falls back to the stagnation point. Additionally, pseudo-stagnation point’s displacement is inversely related to cone’s bluntness, and an increase in angle of attack augments separation from stagnation point on both windward and leeward surfaces.\n
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\n \n\n \n \n Grover, M. S; Valentini, P.; Bisek, N. J.; Jo, S. M.; Davuluri, R.; Martin, A.; Notey, A.; Panesi, M.; Andrienko, D.; and Hanquist, K. M.\n\n\n \n \n \n \n Comparative Analysis of Thermophysics Models for the Simulations of Nonequilibrium Flow.\n \n \n \n\n\n \n\n\n\n In AIAA SciTech 2025 Forum, 2025. AIAA Paper 2025-0641\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{grover2025,\n\ttitle = {Comparative {Analysis} of {Thermophysics} {Models} for the {Simulations} of {Nonequilibrium} {Flow}},\n\tbooktitle = {{AIAA} {SciTech} 2025 {Forum}},\n\tpublisher = {AIAA Paper 2025-0641},\n\tauthor = {Grover, Maninder S and Valentini, Paulo and Bisek, Nicholas J. and Jo, Sung Min and Davuluri, Raghava and Martin, Alexandre and Notey, Aakanksha and Panesi, Marco and Andrienko, Daniil and Hanquist, Kyle M.},\n\tyear = {2025},\n}\n\n\n\n
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\n \n\n \n \n Oveissi, P.; Khokhar, G.; Hanquist, K. M.; and Goel, A.\n\n\n \n \n \n \n Adaptive Combustion Regulation in High-Fidelity Computational Model of Solid Fuel Ramjet.\n \n \n \n\n\n \n\n\n\n In AIAA SciTech 2025 Forum, 2025. AIAA Paper 2025-0352\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n\n\n\n
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@inproceedings{oveissi2025,\n\ttitle = {Adaptive {Combustion} {Regulation} in {High}-{Fidelity} {Computational} {Model} of {Solid} {Fuel} {Ramjet}},\n\tbooktitle = {{AIAA} {SciTech} 2025 {Forum}},\n\tpublisher = {AIAA Paper 2025-0352},\n\tauthor = {Oveissi, Parham and Khokhar, Gohar and Hanquist, Kyle M. and Goel, Ankit},\n\tyear = {2025},\n\tkeywords = {own},\n}\n\n\n\n
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\n \n\n \n \n Oveissi, P.; Goel, A.; Mcbeth, J.; and Hanquist, K. M.\n\n\n \n \n \n \n Learning-based Thrust Regulation of Solid-Fuel Ramjet in Flight Conditions.\n \n \n \n\n\n \n\n\n\n In AIAA SciTech 2025 Forum, 2025. AIAA Paper 2025-2805\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n\n\n\n
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@inproceedings{oveissi2025a,\n\ttitle = {Learning-based {Thrust} {Regulation} of {Solid}-{Fuel} {Ramjet} in {Flight} {Conditions}},\n\tbooktitle = {{AIAA} {SciTech} 2025 {Forum}},\n\tpublisher = {AIAA Paper 2025-2805},\n\tauthor = {Oveissi, Parham and Goel, Ankit and Mcbeth, Joshua and Hanquist, Kyle M.},\n\tyear = {2025},\n\tkeywords = {own},\n}\n\n\n\n
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\n \n\n \n \n Nelson-Melby, L.; Khokhar, G.; Hanquist, K. M.; Peck, M.; Bemis, B.; Juliano, T. J; and Gordeyev, S.\n\n\n \n \n \n \n Numerical Study for Design of Experiment on Aero-Optical Effects of Crossflow Waves in Hypersonic Flow.\n \n \n \n\n\n \n\n\n\n In AIAA SciTech 2025 Forum, 2025. AIAA Paper 2025-2769\n \n\n\n\n
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@inproceedings{nelson-melby2025,\n\ttitle = {Numerical {Study} for {Design} of {Experiment} on {Aero}-{Optical} {Effects} of {Crossflow} {Waves} in {Hypersonic} {Flow}},\n\tbooktitle = {{AIAA} {SciTech} 2025 {Forum}},\n\tpublisher = {AIAA Paper 2025-2769},\n\tauthor = {Nelson-Melby, Leif and Khokhar, Gohar and Hanquist, Kyle M. and Peck, Madeline and Bemis, Benjamin and Juliano, Thomas J and Gordeyev, Stanislav},\n\tyear = {2025},\n\tkeywords = {own},\n}\n\n\n\n
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\n \n\n \n \n Khokhar, G.; McBeth, J.; Hanquist, K. M.; Oveissi, P.; and Goel, A.\n\n\n \n \n \n \n Investigation of Solid Fuel Ramjets using Analytical Theory and Computational Fluid Dynamics.\n \n \n \n\n\n \n\n\n\n In AIAA SciTech 2025 Forum, 2025. AIAA Paper 2025-0392\n \n\n\n\n
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@inproceedings{mcbeth2025,\n\ttitle = {Investigation of {Solid} {Fuel} {Ramjets} using {Analytical} {Theory} and {Computational} {Fluid} {Dynamics}},\n\tbooktitle = {{AIAA} {SciTech} 2025 {Forum}},\n\tpublisher = {AIAA Paper 2025-0392},\n\tauthor = {Khokhar, Gohar and McBeth, Joshua and Hanquist, Kyle M. and Oveissi, Parham and Goel, Ankit},\n\tyear = {2025},\n\tkeywords = {own},\n}\n\n\n\n
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\n \n\n \n \n Paxton, O.\n\n\n \n \n \n \n Investigation into electron transpiration cooling in hypersonic flows.\n \n \n \n\n\n \n\n\n\n Ph.D. Thesis, The University of Queensland, Brisbane, Austrailia, 2024.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@phdthesis{paxton2024,\n\taddress = {Brisbane, Austrailia},\n\ttitle = {Investigation into electron transpiration cooling in hypersonic flows},\n\tschool = {The University of Queensland},\n\tauthor = {Paxton, O.},\n\tyear = {2024},\n}\n\n\n\n
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\n \n\n \n \n Kinsey, B.; Skora, A.; Mokler, M.; Wheeler, M.; Dahl, K.; Craig, S. A.; Portoni, P.; Basore, K.; Strauss, T.; Dean, T.; Arndt, A.; and Wernz, S.\n\n\n \n \n \n \n \n Measurement of Heat Flux on a 3D Printed Hemisphere With IR Thermography.\n \n \n \n \n\n\n \n\n\n\n In AIAA AVIATION FORUM AND ASCEND 2024, Las Vegas, Nevada, July 2024. American Institute of Aeronautics and Astronautics\n \n\n\n\n
\n\n\n\n \n \n \"MeasurementPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{kinsey_measurement_2024,\n\taddress = {Las Vegas, Nevada},\n\ttitle = {Measurement of {Heat} {Flux} on a {3D} {Printed} {Hemisphere} {With} {IR} {Thermography}},\n\tisbn = {978-1-62410-716-0},\n\turl = {https://arc.aiaa.org/doi/10.2514/6.2024-4284},\n\tdoi = {10.2514/6.2024-4284},\n\tlanguage = {en},\n\turldate = {2025-05-22},\n\tbooktitle = {{AIAA} {AVIATION} {FORUM} {AND} {ASCEND} 2024},\n\tpublisher = {American Institute of Aeronautics and Astronautics},\n\tauthor = {Kinsey, Brian and Skora, Adam and Mokler, Matthew and Wheeler, Makena and Dahl, Kirk and Craig, Stuart A. and Portoni, Phillip and Basore, Kevin and Strauss, Tristan and Dean, Tyler and Arndt, Alexander and Wernz, Stefan},\n\tmonth = jul,\n\tyear = {2024},\n}\n\n\n\n
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\n \n\n \n \n Larsen, A.; Tumuklu, O.; and Hanquist, K. M.\n\n\n \n \n \n \n Theory and Simulation of High-Temperature Gas in Shock Tubes.\n \n \n \n\n\n \n\n\n\n 2024.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n\n\n\n
\n 
@misc{larsen2024a,\n\ttitle = {Theory and {Simulation} of {High}-{Temperature} {Gas} in {Shock} {Tubes}},\n\tauthor = {Larsen, Aaron and Tumuklu, Ozgur and Hanquist, Kyle M.},\n\tyear = {2024},\n\tkeywords = {own, presentation},\n}\n\n\n\n
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\n \n\n \n \n Larsen, A.; and Hanquist, K. M.\n\n\n \n \n \n \n Vibrational State-to-State Thermochemical Modeling of High-Temperature Oxgyen Flows.\n \n \n \n\n\n \n\n\n\n 2024.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n\n\n\n
\n 
@misc{larsen2024,\n\ttitle = {Vibrational {State}-to-{State} {Thermochemical} {Modeling} of {High}-{Temperature} {Oxgyen} {Flows}},\n\tauthor = {Larsen, Aaron and Hanquist, Kyle M.},\n\tyear = {2024},\n\tkeywords = {own, presentation},\n}\n\n\n\n
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\n \n\n \n \n Hanquist, K. M.; Khokhar, G.; Larsen, A.; Liza, M. E.; White, A.; Nelson-Melby, L.; Schmidt, S.; Fraijo, D.; Horth, S.; and Tuba, A.\n\n\n \n \n \n \n \n Ongoing work using SU2 for hypersonic applications.\n \n \n \n \n\n\n \n\n\n\n 2024.\n \n\n\n\n
\n\n\n\n \n \n \"OngoingPaper\n  \n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n\n\n\n
\n 
@misc{hanquist2024,\n\ttitle = {Ongoing work using {SU2} for hypersonic applications},\n\turl = {https://su2foundation.org/su2conference2024/},\n\tauthor = {Hanquist, Kyle M. and Khokhar, Gohar and Larsen, Aaron and Liza, Martin E. and White, Avery and Nelson-Melby, Leif and Schmidt, Sydney and Fraijo, Daniel and Horth, Shelby and Tuba, Ana},\n\tyear = {2024},\n\tkeywords = {own, presentation},\n}\n\n\n\n
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\n \n\n \n \n Liza, M. E.; and Hanquist, K. M.\n\n\n \n \n \n \n Numerical Investigation of Nonequilibrium Effects on Aero-Optics in Hypersonic Flows.\n \n \n \n\n\n \n\n\n\n Journal of Thermophysics and Heat Transfer (under review). 2024.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n\n\n\n
\n 
@article{liza2024,\n\ttitle = {Numerical {Investigation} of {Nonequilibrium} {Effects} on {Aero}-{Optics} in {Hypersonic} {Flows}},\n\tjournal = {Journal of Thermophysics and Heat Transfer (under review)},\n\tauthor = {Liza, Martin E. and Hanquist, Kyle M.},\n\tyear = {2024},\n\tkeywords = {own},\n}\n\n\n\n
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\n \n\n \n \n Oveissi, P.; Goel, A.; Tumuklu, O.; and Hanquist, K. M.\n\n\n \n \n \n \n Adaptive Combustion Regulation in Solid Fuel Ramjet.\n \n \n \n\n\n \n\n\n\n In AIAA SCITECH 2024 Forum, 2024. AIAA Paper 2024-0743\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n\n\n\n
\n 
@inproceedings{oveissi2024,\n\ttitle = {Adaptive {Combustion} {Regulation} in {Solid} {Fuel} {Ramjet}},\n\tdoi = {10.2514/6.2024-0743},\n\tabstract = {Control of the combustion process under hypersonic conditions remains a challenging problem. In this paper, we investigate the application of a data-driven, learning-based control technique to regulate a combustion process evolving inside a solid fuel ramjet to regulate the generated thrust under unknown operating conditions. A computational model to simulate the combustion dynamics is developed by combining compressible flow theory with equilibrium chemistry. The computational model is simulated to ascertain the combustion dynamics' stability and establish the engine's operational envelope. Based on retrospective cost optimization, an online learning controller is then integrated with the computational model to regulate the generated thrust. Numerical simulation results are presented to demonstrate the robustness of the adaptive control system.},\n\tbooktitle = {{AIAA} {SCITECH} 2024 {Forum}},\n\tpublisher = {AIAA Paper 2024-0743},\n\tauthor = {Oveissi, Parham and Goel, Ankit and Tumuklu, Ozgur and Hanquist, Kyle M.},\n\tyear = {2024},\n\tkeywords = {own},\n}\n\n\n\n
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\n Control of the combustion process under hypersonic conditions remains a challenging problem. In this paper, we investigate the application of a data-driven, learning-based control technique to regulate a combustion process evolving inside a solid fuel ramjet to regulate the generated thrust under unknown operating conditions. A computational model to simulate the combustion dynamics is developed by combining compressible flow theory with equilibrium chemistry. The computational model is simulated to ascertain the combustion dynamics' stability and establish the engine's operational envelope. Based on retrospective cost optimization, an online learning controller is then integrated with the computational model to regulate the generated thrust. Numerical simulation results are presented to demonstrate the robustness of the adaptive control system.\n
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\n \n\n \n \n Tumuklu, O.; and Hanquist, K. M.\n\n\n \n \n \n \n Hypersonic turbulence wake modeling from rarefied to continuum regimes.\n \n \n \n\n\n \n\n\n\n AIP Conference Proceedings, 2996(1). 2024.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n\n\n\n
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@article{tumuklu2024,\n\ttitle = {Hypersonic turbulence wake modeling from rarefied to continuum regimes},\n\tvolume = {2996},\n\tdoi = {10.1063/5.0187575},\n\tabstract = {Hypersonic flows over a cylinder are studied to investigate the unsteady characteristics of rarefied and continuum turbulent wake flows. To do this end, an open-source DSMC solver, SPARTA, is used to capture large gradients associated with shock expansion waves separation region interactions especially in the wake region. Conversely, continuum simulations are carried out using an open-source continuum non-equilibrium solver, SU2-NEMO, for relatively low-pressure rarefied nature of flows with a freestream pressure of up to 100 Pa. Comparisons were made using SPARTA and SU2-NEMO at moderately low freestream pressures of 100 Pa for NS and very good agreement is achieved using continuum and rarefied solvers, indicating that DSMC and continuum numerical parameters are accurately selected. Numerical probes are inserted at various locations to study the temporal and turbulence characteristics by performing ensemble averaging each time step of DSMC. Consistent with previous numerical studies, x-velocity, y-velocity, and cross-velocity fluctuations are mostly dominant in the wake, bow, and tail shock region. For higher pressure cases, temporal characteristics of residuals are reported to calculate the frequency of oscillations seen in the wake with various Reynolds numbers (Re). The frequency of oscillations is found to be in relatively good agreement with previous experimental measurements and tends to increase with Re.},\n\tlanguage = {en},\n\tnumber = {1},\n\tjournal = {AIP Conference Proceedings},\n\tauthor = {Tumuklu, Ozgur and Hanquist, Kyle M.},\n\tyear = {2024},\n\tkeywords = {own},\n}\n\n\n\n
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\n Hypersonic flows over a cylinder are studied to investigate the unsteady characteristics of rarefied and continuum turbulent wake flows. To do this end, an open-source DSMC solver, SPARTA, is used to capture large gradients associated with shock expansion waves separation region interactions especially in the wake region. Conversely, continuum simulations are carried out using an open-source continuum non-equilibrium solver, SU2-NEMO, for relatively low-pressure rarefied nature of flows with a freestream pressure of up to 100 Pa. Comparisons were made using SPARTA and SU2-NEMO at moderately low freestream pressures of 100 Pa for NS and very good agreement is achieved using continuum and rarefied solvers, indicating that DSMC and continuum numerical parameters are accurately selected. Numerical probes are inserted at various locations to study the temporal and turbulence characteristics by performing ensemble averaging each time step of DSMC. Consistent with previous numerical studies, x-velocity, y-velocity, and cross-velocity fluctuations are mostly dominant in the wake, bow, and tail shock region. For higher pressure cases, temporal characteristics of residuals are reported to calculate the frequency of oscillations seen in the wake with various Reynolds numbers (Re). The frequency of oscillations is found to be in relatively good agreement with previous experimental measurements and tends to increase with Re.\n
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\n \n\n \n \n Tumuklu, O.\n\n\n \n \n \n \n Effect of Spanwise Instabilities on Hypersonic Flows.\n \n \n \n\n\n \n\n\n\n In AIAA AVIATION FORUM AND ASCEND 2024, 2024. AIAA Paper 2024-3834\n _eprint: https://arc.aiaa.org/doi/pdf/10.2514/6.2024-3834\n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{tumuklu2024a,\n\ttitle = {Effect of {Spanwise} {Instabilities} on {Hypersonic} {Flows}},\n\tdoi = {10.2514/6.2024-3834},\n\tabstract = {This study investigates hypersonic Mach 7.1 flows with varying unit Reynolds numbers of 5.2E+4, 1.04E+5, and 4.14E+5 1/m over a double wedge with wedge angles of 0/30◦, 5/30◦, and 30/45◦ using both 2D and 3D configurations. Significant influences of wedge angles on shock interactions, flow dynamics, and surface parameters are observed. A detailed analysis of the temporal characteristics of the flow and surface fields is carried out. The characteristics of self-induced spanwise instabilities in the relatively large separation region are closely examined. Increasing the wedge angles led to a nonlinear increase in spanwise instabilities.},\n\turldate = {2024-09-16},\n\tbooktitle = {{AIAA} {AVIATION} {FORUM} {AND} {ASCEND} 2024},\n\tpublisher = {AIAA Paper 2024-3834},\n\tauthor = {Tumuklu, Ozgur},\n\tyear = {2024},\n\tdoi = {10.2514/6.2024-3834},\n\tnote = {\\_eprint: https://arc.aiaa.org/doi/pdf/10.2514/6.2024-3834},\n}\n\n\n\n\n\n\n\n\n\n\n\n
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\n This study investigates hypersonic Mach 7.1 flows with varying unit Reynolds numbers of 5.2E+4, 1.04E+5, and 4.14E+5 1/m over a double wedge with wedge angles of 0/30◦, 5/30◦, and 30/45◦ using both 2D and 3D configurations. Significant influences of wedge angles on shock interactions, flow dynamics, and surface parameters are observed. A detailed analysis of the temporal characteristics of the flow and surface fields is carried out. The characteristics of self-induced spanwise instabilities in the relatively large separation region are closely examined. Increasing the wedge angles led to a nonlinear increase in spanwise instabilities.\n
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\n \n\n \n \n Codron, D. A.; Thelen, R.; Kennedy, R.; and Pearson, J. H.\n\n\n \n \n \n \n Development of a Small-Scale Arc Jet Facility for Plasma Diagnostic Research and Material Testing.\n \n \n \n\n\n \n\n\n\n In AIAA Aviation, 2024. \n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{codron2024,\n\ttitle = {Development of a {Small}-{Scale} {Arc} {Jet} {Facility} for {Plasma} {Diagnostic} {Research} and {Material} {Testing}},\n\tbooktitle = {{AIAA} {Aviation}},\n\tauthor = {Codron, Douglas A. and Thelen, Ryan and Kennedy, Ryan and Pearson, Justin H.},\n\tyear = {2024},\n}\n\n\n\n
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\n \n\n \n \n Gangemi, G. M.; Hillewaert, K.; Magin, T.; and Laguna, A. A.\n\n\n \n \n \n \n Multicomponent simulation of plasma-sheath formation in presence of an emitting surface.\n \n \n \n\n\n \n\n\n\n In AIAA SCITECH 2024 Forum, 2024. AIAA Paper 2024-2605\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{gangemi2024,\n\ttitle = {Multicomponent simulation of plasma-sheath formation in presence of an emitting surface},\n\tabstract = {In a wall-confined environment, the plasma behaviour can be identified by dividing the domain in two main regions: the bulk, where the quasi-neutrality prevails (the charge density is close to zero) and the sheath region near the walls, where positive space charge is built. This phenomenon is due to a higher mobility of electrons, creating an electric potential structure that accelerates the ions towards the surface and repels the electrons. In this work we present a multicomponent approach to the problem of the formation of sheath in the presence of a thermionic emissive surface: this type of materials are of particular interest in the modelling of emissive probes or in novel thermal protection systems strategies that include the use of electron transpiration cooling materials for hypersonic leading edges.},\n\turldate = {2024-04-12},\n\tbooktitle = {{AIAA} {SCITECH} 2024 {Forum}},\n\tpublisher = {AIAA Paper 2024-2605},\n\tauthor = {Gangemi, Giuseppe Matteo and Hillewaert, Koen and Magin, Thierry and Laguna, Alejandro Alvarez},\n\tyear = {2024},\n}\n\n\n\n\n\n\n\n\n\n\n\n
\n
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\n In a wall-confined environment, the plasma behaviour can be identified by dividing the domain in two main regions: the bulk, where the quasi-neutrality prevails (the charge density is close to zero) and the sheath region near the walls, where positive space charge is built. This phenomenon is due to a higher mobility of electrons, creating an electric potential structure that accelerates the ions towards the surface and repels the electrons. In this work we present a multicomponent approach to the problem of the formation of sheath in the presence of a thermionic emissive surface: this type of materials are of particular interest in the modelling of emissive probes or in novel thermal protection systems strategies that include the use of electron transpiration cooling materials for hypersonic leading edges.\n
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\n \n\n \n \n Morton, S. A.; and Cummings, R. M.\n\n\n \n \n \n \n CFD 2030: Hypersonic Modeling & Simulation Grand Challenge.\n \n \n \n\n\n \n\n\n\n In AIAA SCITECH 2024 Forum, 2024. AIAA Paper 2024-0683\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{morton2024,\n\ttitle = {{CFD} 2030: {Hypersonic} {Modeling} \\& {Simulation} {Grand} {Challenge}},\n\tshorttitle = {{CFD} 2030},\n\tabstract = {This paper outlines a grand challenge for simulation of hypersonic vehicles to add to the set of grand challenges the AIAA CFD2030 Integrating Committee has proposed for maneuvering aircraft{\\textasciicircum}1, turbo-machinery engines{\\textasciicircum}2, and space launch vehicles{\\textasciicircum}3. Two classes of hypersonic vehicles are proposed for the hypersonic grand challenge to highlight a large number of the physical modeling challenges experienced in hypersonic vehicle flight. The two vehicle classes are referred to as the Boost Glide Concept (BGC) and the Air-Breathing Cruiser (ABC). A detailed representation of the BGC and ABC required simulation capabilities is presented, as well as a set of sub-challenges for each. Finally, a timeline is presented that completes the hypersonic grand challenge demonstrations by the end of 2030.},\n\turldate = {2024-04-12},\n\tbooktitle = {{AIAA} {SCITECH} 2024 {Forum}},\n\tpublisher = {AIAA Paper 2024-0683},\n\tauthor = {Morton, Scott A. and Cummings, Russell M.},\n\tyear = {2024},\n}\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n
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\n This paper outlines a grand challenge for simulation of hypersonic vehicles to add to the set of grand challenges the AIAA CFD2030 Integrating Committee has proposed for maneuvering aircraft\\textasciicircum1, turbo-machinery engines\\textasciicircum2, and space launch vehicles\\textasciicircum3. Two classes of hypersonic vehicles are proposed for the hypersonic grand challenge to highlight a large number of the physical modeling challenges experienced in hypersonic vehicle flight. The two vehicle classes are referred to as the Boost Glide Concept (BGC) and the Air-Breathing Cruiser (ABC). A detailed representation of the BGC and ABC required simulation capabilities is presented, as well as a set of sub-challenges for each. Finally, a timeline is presented that completes the hypersonic grand challenge demonstrations by the end of 2030.\n
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\n \n\n \n \n Jin, H.; Mi, Z.; Li, Z.; Wu, X.; Sui, Z.; and Dong, P.\n\n\n \n \n \n \n Investigation of the influence mechanism of hypersonic flow field environment on thermionic emission efficiency.\n \n \n \n\n\n \n\n\n\n International Journal of Heat and Mass Transfer, 226. July 2024.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{jin2024,\n\ttitle = {Investigation of the influence mechanism of hypersonic flow field environment on thermionic emission efficiency},\n\tvolume = {226},\n\tissn = {0017-9310},\n\tdoi = {10.1016/j.ijheatmasstransfer.2024.125502},\n\tabstract = {Electron Transpiration Cooling (ETC) is a novel thermal management method that utilizes thermionic emission to cool the leading edge surface of a hypersonic vehicle. Establishing a thermionic emission model that accounts for the hypersonic flow field environment is imperative for accurately predicting the thermal protection efficiency of ETC. A thermionic emission dual-sheath model was established, considering the impact of hypersonic non-equilibrium flow field particle parameters on thermal electron emission. The virtual cathode threshold was obtained through numerical analysis, considering the influence of particles parameters and surface thermoelectric material parameters in a non-equilibrium flow field. Distribution of sheath potential and particle number density in plasma sheath region were performed at a range of conditions. Thermionic emission efficiency approached 80 \\% as the plasma ion density was 5 × 20 m−3 and the work function was 2 eV. The results showed that plasma ions have different degrees of neutralization effect on thermal emission electrons depending on the flow field and surface material characteristics, ultimately causing varying surface thermionic emission efficiency.},\n\turldate = {2024-04-05},\n\tjournal = {International Journal of Heat and Mass Transfer},\n\tauthor = {Jin, Hua and Mi, Zhitong and Li, Zhuoran and Wu, Xiao and Sui, Zhuochen and Dong, Pan},\n\tmonth = jul,\n\tyear = {2024},\n\tkeywords = {Dual-sheath model, Electron transpiration cooling (ETC), Hypersonic vehicle, Thermal management, Thermionic emission},\n}\n\n\n\n\n\n\n\n
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\n Electron Transpiration Cooling (ETC) is a novel thermal management method that utilizes thermionic emission to cool the leading edge surface of a hypersonic vehicle. Establishing a thermionic emission model that accounts for the hypersonic flow field environment is imperative for accurately predicting the thermal protection efficiency of ETC. A thermionic emission dual-sheath model was established, considering the impact of hypersonic non-equilibrium flow field particle parameters on thermal electron emission. The virtual cathode threshold was obtained through numerical analysis, considering the influence of particles parameters and surface thermoelectric material parameters in a non-equilibrium flow field. Distribution of sheath potential and particle number density in plasma sheath region were performed at a range of conditions. Thermionic emission efficiency approached 80 % as the plasma ion density was 5 × 20 m−3 and the work function was 2 eV. The results showed that plasma ions have different degrees of neutralization effect on thermal emission electrons depending on the flow field and surface material characteristics, ultimately causing varying surface thermionic emission efficiency.\n
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\n  \n 2023\n \n \n (24)\n \n \n
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\n \n\n \n \n \n\n\n \n \n \n \n \n Vulcan Launch Systems User's Guide.\n \n \n \n \n\n\n \n\n\n\n October 2023.\n \n\n\n\n
\n\n\n\n \n \n \"VulcanPaper\n  \n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@misc{vulcan2023,\n\ttitle = {Vulcan {Launch} {Systems} {User}'s {Guide}},\n\turl = {https://www.ulalaunch.com/docs/default-source/default-document-library/2023_vulcan_user_guide.pdf?sfvrsn=37856b50_1},\n\tmonth = oct,\n\tyear = {2023},\n}\n\n\n\n
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\n \n\n \n \n Gupta, A.; Mesalles Ripoll, P.; Campbell, N. S.; and Argrow, B.\n\n\n \n \n \n \n \n Assessment of optical propagation models with application to hypersonic entry.\n \n \n \n \n\n\n \n\n\n\n In AIAA SCITECH 2023 forum, Reston, Virginia, January 2023. American Institute of Aeronautics and Astronautics\n \n\n\n\n
\n\n\n\n \n \n \"AssessmentPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@inproceedings{Gupta2023,\n\taddress = {Reston, Virginia},\n\ttitle = {Assessment of optical propagation models with application to hypersonic entry},\n\tisbn = {978-1-62410-699-6},\n\turl = {https://arc.aiaa.org/doi/10.2514/6.2023-0817},\n\tdoi = {10.2514/6.2023-0817},\n\tbooktitle = {{AIAA} {SCITECH} 2023 forum},\n\tpublisher = {American Institute of Aeronautics and Astronautics},\n\tauthor = {Gupta, Anubhav and Mesalles Ripoll, Pol and Campbell, Nicholas S. and Argrow, Brian},\n\tmonth = jan,\n\tyear = {2023},\n}\n\n\n\n
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\n \n\n \n \n DeBoskey, R. D.; Kessler, D. A.; Bojko, B. T.; Johnson, R. F.; and Goodwin, G. B.\n\n\n \n \n \n \n The Influence of Chemical Reaction Models on Combustion Dynamics in an Opposed-Flow Solid Fuel Burner.\n \n \n \n\n\n \n\n\n\n In AIAA SCITECH 2023 Forum, 2023. AIAA Paper 2023-0161\n _eprint: https://arc.aiaa.org/doi/pdf/10.2514/6.2023-0161\n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{deboskey2023,\n\ttitle = {The {Influence} of {Chemical} {Reaction} {Models} on {Combustion} {Dynamics} in an {Opposed}-{Flow} {Solid} {Fuel} {Burner}},\n\tdoi = {10.2514/6.2023-0161},\n\tabstract = {View Video Presentation: https://doi.org/10.2514/6.2023-0161.vidWe describe the differences in the combustion behavior within a model opposed-flow solid fuel burner produced by three different chemical reaction models: a two-step global mechanism, a six-step global mechanism, and a pressure-comprehensive skeletal model, all of which assume butadiene as the primary fuel source. Details of the implementation of these models in conjunction with an equilibrium interfacial pyrolysis model for the solid gas phase change process are provided. Of particular interest are the differences in flame structure and dynamics predicted by each reaction model in comparison to the performance benefits gained by model simplifications. We provide some observations regarding the use of these global reaction models in a purely non-premixed combustion setting. A preliminary flamelet generated manifold is presented to be explored in future work.},\n\turldate = {2024-05-29},\n\tbooktitle = {{AIAA} {SCITECH} 2023 {Forum}},\n\tpublisher = {AIAA Paper 2023-0161},\n\tauthor = {DeBoskey, Ryan D. and Kessler, David A. and Bojko, Brian T. and Johnson, Ryan F. and Goodwin, Gabriel B.},\n\tyear = {2023},\n\tnote = {\\_eprint: https://arc.aiaa.org/doi/pdf/10.2514/6.2023-0161},\n}\n\n\n\n\n\n\n\n\n\n\n\n
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\n View Video Presentation: https://doi.org/10.2514/6.2023-0161.vidWe describe the differences in the combustion behavior within a model opposed-flow solid fuel burner produced by three different chemical reaction models: a two-step global mechanism, a six-step global mechanism, and a pressure-comprehensive skeletal model, all of which assume butadiene as the primary fuel source. Details of the implementation of these models in conjunction with an equilibrium interfacial pyrolysis model for the solid gas phase change process are provided. Of particular interest are the differences in flame structure and dynamics predicted by each reaction model in comparison to the performance benefits gained by model simplifications. We provide some observations regarding the use of these global reaction models in a purely non-premixed combustion setting. A preliminary flamelet generated manifold is presented to be explored in future work.\n
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\n \n\n \n \n Maier, W. T.; Needels, J. T.; Alonso, J. J; Morgado, F.; Garbacz, C.; Fossati, M.; Tumuklu, O.; and Hanquist, K. M\n\n\n \n \n \n \n Development of Physical and Numerical Nonequilibrium Modeling Capabilities within the SU2-NEMO Code.\n \n \n \n\n\n \n\n\n\n In 2023. AIAA Paper 2023-3488\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n\n\n\n
\n 
@inproceedings{maier2023,\n\ttitle = {Development of {Physical} and {Numerical} {Nonequilibrium} {Modeling} {Capabilities} within the {SU2}-{NEMO} {Code}},\n\tdoi = {10.2514/6.2023-3488},\n\tpublisher = {AIAA Paper 2023-3488},\n\tauthor = {Maier, Walter T. and Needels, Jacob T. and Alonso, Juan J and Morgado, Fabio and Garbacz, Catarina and Fossati, Marco and Tumuklu, Ozgur and Hanquist, Kyle M},\n\tyear = {2023},\n\tkeywords = {own},\n}\n\n\n\n\n\n\n\n\n\n\n\n
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\n \n\n \n \n Thompson, K. B.; Nishikawa, H.; and Padway, E.\n\n\n \n \n \n \n Economical Third-Order Methods for Accurate Surface Heating Predictions on Simplex Element Meshes.\n \n \n \n\n\n \n\n\n\n In AIAA SCITECH 2023 Forum, 2023. AIAA Paper 2023-2629\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{thompson2023,\n\ttitle = {Economical {Third}-{Order} {Methods} for {Accurate} {Surface} {Heating} {Predictions} on {Simplex} {Element} {Meshes}},\n\tdoi = {10.2514/6.2023-2629},\n\tabstract = {View Video Presentation: https://doi.org/10.2514/6.2023-2629.vidA node-centered, edge-based finite volume discretization of the compressible Navier-Stokes equations is presented with the heat flux reformulated as a first-order system. A dissipation vector is derived for the reformulated system, such that the heat flux can be upgraded to O(h{\\textasciicircum}3) on simplex element meshes in the same fashion as the inviscid fluxes. The method of manufactured solutions is used to demonstrate this uniform order property in heat flux. This new system is shown to efficiently produce accurate surface heating predictions in hypersonic flow using an anisotropic simplex element mesh, achieving O(h{\\textasciicircum}3) accuracy at relatively low computational cost compared to similar methods.},\n\turldate = {2024-05-27},\n\tbooktitle = {{AIAA} {SCITECH} 2023 {Forum}},\n\tpublisher = {AIAA Paper 2023-2629},\n\tauthor = {Thompson, Kyle B. and Nishikawa, Hiroaki and Padway, Emmett},\n\tyear = {2023},\n}\n\n\n\n\n\n\n\n
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\n View Video Presentation: https://doi.org/10.2514/6.2023-2629.vidA node-centered, edge-based finite volume discretization of the compressible Navier-Stokes equations is presented with the heat flux reformulated as a first-order system. A dissipation vector is derived for the reformulated system, such that the heat flux can be upgraded to O(h\\textasciicircum3) on simplex element meshes in the same fashion as the inviscid fluxes. The method of manufactured solutions is used to demonstrate this uniform order property in heat flux. This new system is shown to efficiently produce accurate surface heating predictions in hypersonic flow using an anisotropic simplex element mesh, achieving O(h\\textasciicircum3) accuracy at relatively low computational cost compared to similar methods.\n
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\n \n\n \n \n Gollapudi, S.; Suchicital, C.; Li, J.; and Viehland, D.\n\n\n \n \n \n \n Realization of electron transpiration cooling: LaB6 heated by a plasma glow.\n \n \n \n\n\n \n\n\n\n Applied Physics Letters, 123(10): 101602. September 2023.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{gollapudi2023,\n\ttitle = {Realization of electron transpiration cooling: {LaB6} heated by a plasma glow},\n\tvolume = {123},\n\tissn = {0003-6951, 1077-3118},\n\tshorttitle = {Realization of electron transpiration cooling},\n\tdoi = {10.1063/5.0163560},\n\tabstract = {Electron transpiration cooling has previously been predicted to be an alternative cooling mechanism for leading edges of aerospace platforms traveling at extreme velocities, where thermoelectric materials shaped as leading edges manage heat loads. Here, thermo-electron emitting LaB6 ceramics with blunt edges were placed between two conical-shaped electrodes, and a plasma glow was ignited to heat the sample. Analysis of current–voltage (I–V) curves demonstrated that insertion of LaB6 into the plasma column resulted in an increase in the electron density of the plasma, evidencing thermally stimulated electron emission. With increasing sample temperature to 1200 K, Dne increased by \\$4 Â 1010 \\#/cm3, the electron temperature (Te) decreased from \\$8 eV (1000 K) to 2.5 eV, and the emission begins to appear to become space charge-limited. Richardson’s analysis of the temperature dependence of the electron emission in the region of ion saturation, yielded an activation energy consistent with the work function of LaB6. Modulation of the LaB6 surface temperature (DT ¼ 10 K) and the plasma current (DI ¼ 70 lA) under electric voltage (80 V) applied between the sample and current probe was demonstrated. The results show for the first time the feasibility of electron transpiration cooling effects under plasma conditions similar to that of aerothermal environments.},\n\tlanguage = {en},\n\tnumber = {10},\n\turldate = {2023-10-30},\n\tjournal = {Applied Physics Letters},\n\tauthor = {Gollapudi, Sreenivasulu and Suchicital, Carlos and Li, Jie-Fang and Viehland, D.},\n\tmonth = sep,\n\tyear = {2023},\n\tpages = {101602},\n}\n\n\n\n
\n
\n\n\n
\n Electron transpiration cooling has previously been predicted to be an alternative cooling mechanism for leading edges of aerospace platforms traveling at extreme velocities, where thermoelectric materials shaped as leading edges manage heat loads. Here, thermo-electron emitting LaB6 ceramics with blunt edges were placed between two conical-shaped electrodes, and a plasma glow was ignited to heat the sample. Analysis of current–voltage (I–V) curves demonstrated that insertion of LaB6 into the plasma column resulted in an increase in the electron density of the plasma, evidencing thermally stimulated electron emission. With increasing sample temperature to 1200 K, Dne increased by $4 Â 1010 #/cm3, the electron temperature (Te) decreased from $8 eV (1000 K) to 2.5 eV, and the emission begins to appear to become space charge-limited. Richardson’s analysis of the temperature dependence of the electron emission in the region of ion saturation, yielded an activation energy consistent with the work function of LaB6. Modulation of the LaB6 surface temperature (DT ¼ 10 K) and the plasma current (DI ¼ 70 lA) under electric voltage (80 V) applied between the sample and current probe was demonstrated. The results show for the first time the feasibility of electron transpiration cooling effects under plasma conditions similar to that of aerothermal environments.\n
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\n \n\n \n \n Moritz, J.; Heuraux, S.; Lemoine, N.; Lesur, M.; Gravier, E.; Brochard, F.; Marot, L.; and Hiret, P.\n\n\n \n \n \n \n Thermionic emission of a tungsten surface in high heat flux plasma: PIC simulations.\n \n \n \n\n\n \n\n\n\n Physics of Plasmas, 30(8). August 2023.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{moritz2023,\n\ttitle = {Thermionic emission of a tungsten surface in high heat flux plasma: {PIC} simulations},\n\tvolume = {30},\n\tshorttitle = {Thermionic emission of a tungsten surface in high heat flux plasma},\n\tdoi = {10.1063/5.0160767},\n\tabstract = {The surface temperature of a tungsten surface facing hot hydrogen plasma is evaluated, thanks to 1d/3v particle-in-cell simulations in floating wall conditions. At each iteration, the plasma heat flux to the cathode is equalized with the outgoing one, which is due to thermionic emission, surface radiation, and heat conduction through the wall. The thermal conductivity is chosen within the range 35–160 W mÀ1 KÀ1 in the different simulations in order to take into account the surface condition. A transition from a cold temperature surface to a hot one arises for a critical thermal conductivity, whose value depends on the plasma parameters. This transition is very abrupt and leads to a space charge limited regime where the thermionic current penetrating the plasma has reached its maximal value and is about three times the Bohm current. Changing the initial conditions in the code, more particularly, the timing of electron emission, can lead to a very different final surface temperature. This history effect and the associated hysteresis are evidenced by means of fluid calculations, which are in a good agreement with the simulation results as well as with previous experimental measurements.},\n\tlanguage = {en},\n\tnumber = {8},\n\turldate = {2024-04-05},\n\tjournal = {Physics of Plasmas},\n\tauthor = {Moritz, J. and Heuraux, S. and Lemoine, N. and Lesur, M. and Gravier, E. and Brochard, F. and Marot, L. and Hiret, P.},\n\tmonth = aug,\n\tyear = {2023},\n}\n\n\n\n\n\n\n\n
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\n The surface temperature of a tungsten surface facing hot hydrogen plasma is evaluated, thanks to 1d/3v particle-in-cell simulations in floating wall conditions. At each iteration, the plasma heat flux to the cathode is equalized with the outgoing one, which is due to thermionic emission, surface radiation, and heat conduction through the wall. The thermal conductivity is chosen within the range 35–160 W mÀ1 KÀ1 in the different simulations in order to take into account the surface condition. A transition from a cold temperature surface to a hot one arises for a critical thermal conductivity, whose value depends on the plasma parameters. This transition is very abrupt and leads to a space charge limited regime where the thermionic current penetrating the plasma has reached its maximal value and is about three times the Bohm current. Changing the initial conditions in the code, more particularly, the timing of electron emission, can lead to a very different final surface temperature. This history effect and the associated hysteresis are evidenced by means of fluid calculations, which are in a good agreement with the simulation results as well as with previous experimental measurements.\n
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\n \n\n \n \n Tumuklu, O.; and Hanquist, K. M.\n\n\n \n \n \n \n Temporal characteristics of hypersonic flows over a double wedge with Reynolds number.\n \n \n \n\n\n \n\n\n\n Physics of Fluids, 35(10). October 2023.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n\n\n\n
\n 
@article{tumuklu2023c,\n\ttitle = {Temporal characteristics of hypersonic flows over a double wedge with {Reynolds} number},\n\tvolume = {35},\n\tdoi = {10.1063/5.0169648},\n\tabstract = {Laminar hypersonic flows at Mach 7.10 with unit Reynolds numbers of    5.2 ×   10 4 ,   1.04 ×   10 5, and    4.14 ×   10 5 m−1 over a 30°/55° double-wedge configuration were studied to investigate the spatial–temporal characteristics of the flow in a time-accurate manner. Close comparisons were made between previous kinetic and current continuum approaches to test the validity of the continuum assumption, especially considering the presence of large gradients associated with shock–shock and shock–boundary layer interactions, as well as spanwise instabilities. Previous results from direct simulation Monte Carlo, which inherently predicts rarefied effects such as velocity slip and temperature jumps, were found to be in very close agreement with the current work, even for the lowest Reynolds number. The impact of velocity slip and temperature jumps on flow and surface parameters was investigated, and comparisons were made with a no-slip and constant temperature wall model. The temporal and spatial variation of two- and three-dimensional flows were thoroughly investigated using two-dimensional (2D), three-dimensional (3D) periodic sidewall boundary conditions, and a full 3D configuration consistent with existing experimental data. Close comparisons among the 2D and 3D cases were made. The characteristics of 2D periodic oscillations were reported for the moderate Reynolds number case for the first time. The presence of spanwise instabilities, even at a relatively low free stream pressure of about 100 Pa, establishes that the flow field depends on spanwise effects and is fully 3D. High-fidelity numerical schlieren videos captured strong spanwise oscillations for 3D configurations.},\n\tnumber = {10},\n\tjournal = {Physics of Fluids},\n\tauthor = {Tumuklu, Ozgur and Hanquist, Kyle M.},\n\tmonth = oct,\n\tyear = {2023},\n\tkeywords = {own},\n}\n\n\n\n
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\n Laminar hypersonic flows at Mach 7.10 with unit Reynolds numbers of 5.2 × 10 4 ,   1.04 × 10 5, and 4.14 × 10 5 m−1 over a 30°/55° double-wedge configuration were studied to investigate the spatial–temporal characteristics of the flow in a time-accurate manner. Close comparisons were made between previous kinetic and current continuum approaches to test the validity of the continuum assumption, especially considering the presence of large gradients associated with shock–shock and shock–boundary layer interactions, as well as spanwise instabilities. Previous results from direct simulation Monte Carlo, which inherently predicts rarefied effects such as velocity slip and temperature jumps, were found to be in very close agreement with the current work, even for the lowest Reynolds number. The impact of velocity slip and temperature jumps on flow and surface parameters was investigated, and comparisons were made with a no-slip and constant temperature wall model. The temporal and spatial variation of two- and three-dimensional flows were thoroughly investigated using two-dimensional (2D), three-dimensional (3D) periodic sidewall boundary conditions, and a full 3D configuration consistent with existing experimental data. Close comparisons among the 2D and 3D cases were made. The characteristics of 2D periodic oscillations were reported for the moderate Reynolds number case for the first time. The presence of spanwise instabilities, even at a relatively low free stream pressure of about 100 Pa, establishes that the flow field depends on spanwise effects and is fully 3D. High-fidelity numerical schlieren videos captured strong spanwise oscillations for 3D configurations.\n
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\n \n\n \n \n Baluckram, V. T.; Fangman, A. J.; and Andrienko, D. A.\n\n\n \n \n \n \n \n Simulation of Oxygen Chemical Kinetics Behind Incident and Reflected Shocks via Master Equation.\n \n \n \n \n\n\n \n\n\n\n Journal of Thermophysics and Heat Transfer, 37(1): 198–212. 2023.\n \n\n\n\n
\n\n\n\n \n \n \"SimulationPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{baluckram2023,\n\ttitle = {Simulation of {Oxygen} {Chemical} {Kinetics} {Behind} {Incident} and {Reflected} {Shocks} via {Master} {Equation}},\n\tvolume = {37},\n\tissn = {0887-8722},\n\turl = {https://doi.org/10.2514/1.T6522},\n\tdoi = {10.2514/1.T6522},\n\tabstract = {A model for simulating postshock conditions using only state-resolved kinetic data of ab initio accuracy is presented. The quasi-classical trajectory method is used to compute a vibrational-specific kinetic database that describes internal energy transfer and dissociation in a nonionizing oxygen mixture. The kinetic database is implemented in a system of master equations and coupled to conservation laws to simulate a series of conditions, including zero-dimensional adiabatic reservoir, one-dimensional postincident, and one-dimensional postreflected shock relaxation. The present results are in excellent agreement with temperature profiles produced by the direct molecular simulation method at a fraction of cost. For the first time, the state-resolved model is applied to model relaxation behind a reflected shock passing through a thermally nonequilibrium gas. Model validation is made via comparisons to the experiments of Ibraguimova et al. (Journal of Chemical Physics, Vol. 139, No. 3, 2013, Paper 034317) and Streicher et al. (Physics of Fluids, Vol. 33, No. 5, 2021, Paper 056107). It is shown that neglecting relaxation in the postincident shock region may lead to nonnegligible errors in determining initial postreflected shock translational and vibrational temperatures, particularly in cases where the test gas is not diluted with an inert species.},\n\tnumber = {1},\n\turldate = {2024-02-29},\n\tjournal = {Journal of Thermophysics and Heat Transfer},\n\tauthor = {Baluckram, Varishth T. and Fangman, Alexander J. and Andrienko, Daniil A.},\n\tyear = {2023},\n\tpages = {198--212},\n}\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n
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\n A model for simulating postshock conditions using only state-resolved kinetic data of ab initio accuracy is presented. The quasi-classical trajectory method is used to compute a vibrational-specific kinetic database that describes internal energy transfer and dissociation in a nonionizing oxygen mixture. The kinetic database is implemented in a system of master equations and coupled to conservation laws to simulate a series of conditions, including zero-dimensional adiabatic reservoir, one-dimensional postincident, and one-dimensional postreflected shock relaxation. The present results are in excellent agreement with temperature profiles produced by the direct molecular simulation method at a fraction of cost. For the first time, the state-resolved model is applied to model relaxation behind a reflected shock passing through a thermally nonequilibrium gas. Model validation is made via comparisons to the experiments of Ibraguimova et al. (Journal of Chemical Physics, Vol. 139, No. 3, 2013, Paper 034317) and Streicher et al. (Physics of Fluids, Vol. 33, No. 5, 2021, Paper 056107). It is shown that neglecting relaxation in the postincident shock region may lead to nonnegligible errors in determining initial postreflected shock translational and vibrational temperatures, particularly in cases where the test gas is not diluted with an inert species.\n
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\n \n\n \n \n Morgado, F.; Garbacz, C.; Tumuklu, O.; Needels, J. T.; Maier, W. T.; Alonso, J. J; Hanquist, K. M.; and Fossati, M.\n\n\n \n \n \n \n Hypersonic Testing & Digital Twins.\n \n \n \n\n\n \n\n\n\n 2023.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n\n\n\n
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@misc{morgado2023,\n\ttitle = {Hypersonic {Testing} \\& {Digital} {Twins}},\n\tauthor = {Morgado, Fábio and Garbacz, Catarina and Tumuklu, Ozgur and Needels, Jacob T. and Maier, Walter T. and Alonso, Juan J and Hanquist, Kyle M. and Fossati, Marco},\n\tyear = {2023},\n\tkeywords = {own, presentation},\n}\n\n\n\n
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\n \n\n \n \n Hanquist, K. M.\n\n\n \n \n \n \n Modeling of Real Gas Effects in Hypersonic Flows.\n \n \n \n\n\n \n\n\n\n 2023.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n\n\n\n
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@misc{hanquist2023e,\n\taddress = {Turbulence Analysis and Simulation Center, Lawrence Livermore National Laboratory},\n\ttype = {Invited {Seminar}},\n\ttitle = {Modeling of {Real} {Gas} {Effects} in {Hypersonic} {Flows}},\n\tauthor = {Hanquist, Kyle M.},\n\tyear = {2023},\n\tkeywords = {invited, own},\n}\n\n\n\n
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\n \n\n \n \n Hanquist, K. M.\n\n\n \n \n \n \n Investigating High-Enthalpy Effects using Computational Modeling.\n \n \n \n\n\n \n\n\n\n 2023.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n\n\n\n
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@misc{hanquist2023d,\n\taddress = {Aerothermodynamics Branch, NASA Ames},\n\ttype = {Invited {Seminar}},\n\ttitle = {Investigating {High}-{Enthalpy} {Effects} using {Computational} {Modeling}},\n\tauthor = {Hanquist, Kyle M.},\n\tyear = {2023},\n\tkeywords = {invited, own},\n}\n\n\n\n
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\n \n\n \n \n Hanquist, K. M.\n\n\n \n \n \n \n Investigating High-Enthalpy Effects in High-Speed Flows using Open-Source Computational Modeling.\n \n \n \n\n\n \n\n\n\n 2023.\n \n\n\n\n
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@misc{hanquist2023b,\n\taddress = {Salt Lake City, UT},\n\ttype = {Invited {Presentation}},\n\ttitle = {Investigating {High}-{Enthalpy} {Effects} in {High}-{Speed} {Flows} using {Open}-{Source} {Computational} {Modeling}},\n\tauthor = {Hanquist, Kyle M.},\n\tyear = {2023},\n\tkeywords = {invited, own},\n}\n\n\n\n
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\n \n\n \n \n Hanquist, K. M.\n\n\n \n \n \n \n Investigating high-enthalpy hypersonic effects using modeling and simulation.\n \n \n \n\n\n \n\n\n\n 2023.\n \n\n\n\n
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@misc{hanquist2023c,\n\taddress = {Department of Aerospace Engineering \\& Mechanics, University of Minnesota},\n\ttype = {Invited {Seminar}},\n\ttitle = {Investigating high-enthalpy hypersonic effects using modeling and simulation},\n\tauthor = {Hanquist, Kyle M.},\n\tyear = {2023},\n\tkeywords = {invited, own},\n}\n\n\n\n
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\n \n\n \n \n Kuppa, M.; Singh, N.; Rostkowski, P.; Ghanem, R.; and Panesi, M.\n\n\n \n \n \n \n Reduced Order Modelling and Quantification of Uncertainty in Non Equilibrium Flows.\n \n \n \n\n\n \n\n\n\n In AIAA AVIATION 2023 Forum, 2023. AIAA Paper 2023-3331\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@inproceedings{kuppa2023,\n\ttitle = {Reduced {Order} {Modelling} and {Quantification} of {Uncertainty} in {Non} {Equilibrium} {Flows}},\n\tdoi = {10.2514/6.2023-3331},\n\tabstract = {View Video Presentation: https://doi.org/10.2514/6.2023-3331.vidThis study investigates uncertainty propagation and sensitivity analysis of state-specific dissociation and excitation rate coefficients in the context of macroscopic quantities of interest such as species mole fraction evolution and quasi-steady-state (QSS) rate coefficient. To accomplish this, an isothermal isochoric zero-dimensional chemical reactor is solved for various bath conditions. To handle the computational complexity of the master equations, three different coarse-graining methods are utilized: a 200-bin energy-based lumping model, a 3-bin energy-based lumping model, and a 10-bin spectral clustering-based model. The results show that while the uncertainty propagation is sensitive to the type of coarse-graining, the spectral clustering method produces the least model error when compared to the other coarse-grained models employed. Moreover, when an uncertainty factor of 5 is applied to the state-specific dissociation rate coefficients, it leads to an approximate ± 10\\% uncertainty range around the nominal values of the QSS rate coefficient. The sensitivity analysis conducted using the 200-bin model reveals that the most influential factor affecting the QSS rate coefficient and dissociation time is the mono-quantum vibrational excitation from low-lying levels. Additionally, at low temperatures, the high-lying dissociation rate coefficients contribute significantly to the uncertainty of the studied quantities, while at high temperatures, the dissociation from low to moderate-lying vibrational energy states plays a crucial role. These findings underscore the critical role played by vibrational excitation in determining the behavior of reactive systems at different temperature regimes.},\n\turldate = {2023-08-08},\n\tbooktitle = {{AIAA} {AVIATION} 2023 {Forum}},\n\tpublisher = {AIAA Paper 2023-3331},\n\tauthor = {Kuppa, Mridula and Singh, Narendra and Rostkowski, Przemyslaw and Ghanem, Roger and Panesi, Marco},\n\tyear = {2023},\n}\n\n\n\n\n\n\n\n\n\n\n\n
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\n View Video Presentation: https://doi.org/10.2514/6.2023-3331.vidThis study investigates uncertainty propagation and sensitivity analysis of state-specific dissociation and excitation rate coefficients in the context of macroscopic quantities of interest such as species mole fraction evolution and quasi-steady-state (QSS) rate coefficient. To accomplish this, an isothermal isochoric zero-dimensional chemical reactor is solved for various bath conditions. To handle the computational complexity of the master equations, three different coarse-graining methods are utilized: a 200-bin energy-based lumping model, a 3-bin energy-based lumping model, and a 10-bin spectral clustering-based model. The results show that while the uncertainty propagation is sensitive to the type of coarse-graining, the spectral clustering method produces the least model error when compared to the other coarse-grained models employed. Moreover, when an uncertainty factor of 5 is applied to the state-specific dissociation rate coefficients, it leads to an approximate ± 10% uncertainty range around the nominal values of the QSS rate coefficient. The sensitivity analysis conducted using the 200-bin model reveals that the most influential factor affecting the QSS rate coefficient and dissociation time is the mono-quantum vibrational excitation from low-lying levels. Additionally, at low temperatures, the high-lying dissociation rate coefficients contribute significantly to the uncertainty of the studied quantities, while at high temperatures, the dissociation from low to moderate-lying vibrational energy states plays a crucial role. These findings underscore the critical role played by vibrational excitation in determining the behavior of reactive systems at different temperature regimes.\n
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\n \n\n \n \n Chaudhry, R. S.; and Boyd, I. D.\n\n\n \n \n \n \n Parametric Comparison of the Park and MMT Chemical Kinetics Models with Multiple Freestream Speeds.\n \n \n \n\n\n \n\n\n\n In AIAA AVIATION 2023 Forum, 2023. AIAA Paper 2023-3621\n _eprint: https://arc.aiaa.org/doi/pdf/10.2514/6.2023-3621\n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@inproceedings{chaudhry2023,\n\ttitle = {Parametric {Comparison} of the {Park} and {MMT} {Chemical} {Kinetics} {Models} with {Multiple} {Freestream} {Speeds}},\n\tdoi = {10.2514/6.2023-3621},\n\tabstract = {View Video Presentation: https://doi.org/10.2514/6.2023-3621.vidThe Modified Marrone-Treanor (MMT) chemical kinetics model, developed using quantum chemistry data, is compared to the Park model for hypersonic blunt cones. A variety of flow configuration parameters are considered: nose radii between 1 and 10 cm, freestream altitudes between 0 and 70 km, and freestream speeds between 3 and 6 km/s. Consistent with previous work, lower altitude conditions are dominated by the dynamics of recombination and yield up to 30\\% higher stagnation heating with Park than MMT, whereas higher altitudes are dominated by dissociation and yield up to 15\\% lower heating with Park than MMT. Freestream speeds of 4 and 5 km/s exhibit the largest difference in stagnation-point heating due to the dominance of oxygen dissociation in these flows. Consistency between the present results and Fay and Riddell’s dissociation enthalpy is also demonstrated. This work describes the effect of gas-phase chemical kinetics on design-relevant flow configurations and the wide range of parameters considered can target experimental validation efforts.},\n\turldate = {2023-08-08},\n\tbooktitle = {{AIAA} {AVIATION} 2023 {Forum}},\n\tpublisher = {AIAA Paper 2023-3621},\n\tauthor = {Chaudhry, Ross S. and Boyd, Iain D.},\n\tyear = {2023},\n\tdoi = {10.2514/6.2023-3621},\n\tnote = {\\_eprint: https://arc.aiaa.org/doi/pdf/10.2514/6.2023-3621},\n}\n\n\n\n
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\n View Video Presentation: https://doi.org/10.2514/6.2023-3621.vidThe Modified Marrone-Treanor (MMT) chemical kinetics model, developed using quantum chemistry data, is compared to the Park model for hypersonic blunt cones. A variety of flow configuration parameters are considered: nose radii between 1 and 10 cm, freestream altitudes between 0 and 70 km, and freestream speeds between 3 and 6 km/s. Consistent with previous work, lower altitude conditions are dominated by the dynamics of recombination and yield up to 30% higher stagnation heating with Park than MMT, whereas higher altitudes are dominated by dissociation and yield up to 15% lower heating with Park than MMT. Freestream speeds of 4 and 5 km/s exhibit the largest difference in stagnation-point heating due to the dominance of oxygen dissociation in these flows. Consistency between the present results and Fay and Riddell’s dissociation enthalpy is also demonstrated. This work describes the effect of gas-phase chemical kinetics on design-relevant flow configurations and the wide range of parameters considered can target experimental validation efforts.\n
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\n \n\n \n \n Torres, E.; Gross, T.; and Schwartzentruber, T. E.\n\n\n \n \n \n \n Implementation of new multi-temperature nonequilibrium air chemistry model for CFD based on first-principles calculations.\n \n \n \n\n\n \n\n\n\n In AIAA AVIATION 2023 Forum, 2023. AIAA Paper 2023-3489\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@inproceedings{torres2023,\n\ttitle = {Implementation of new multi-temperature nonequilibrium air chemistry model for {CFD} based on first-principles calculations},\n\tdoi = {10.2514/6.2023-3489},\n\tabstract = {View Video Presentation: https://doi.org/10.2514/6.2023-3489.vidIn this paper we present recent updates to the Modified Marrone-Treanor thermochemical nonequilibrium model for five-species air, originally developed for computational fluid dynamics calculations of hypersonic flows. The updated (2023) version of the chemistry model used here employs new high-fidelity kinetic rate data for all air reactions (including oxygen/nitrogen/nitric oxide dissociation and Zeldovich exchange reactions) derived from quasi-classical trajectory calculations on {\\textbackslash}emphab initio potential energy surfaces. We first verify the updated chemistry model against first-principles Direct Molecular Simulations by studying nonequilibrium reacting air mixtures in space-homogeneous heat baths representative of high-temperature post-shock conditions. Once validated in these simple scenarios, we employ the model in larger-scale computational fluid dynamics studies of hypersonic flow around a geometry representing a generic flight vehicle. There we compare the Modified Marrone-Treanor predictions against the standard nonequilibrium model by Park. This research demonstrates how complex nonequilibrium chemistry induced by hypersonic flight can be incorporated into accurate and efficient models for large-scale computational fluid dynamics simulations.},\n\turldate = {2023-08-08},\n\tbooktitle = {{AIAA} {AVIATION} 2023 {Forum}},\n\tpublisher = {AIAA Paper 2023-3489},\n\tauthor = {Torres, Erik and Gross, Thomas and Schwartzentruber, Thomas E.},\n\tyear = {2023},\n}\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n
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\n View Video Presentation: https://doi.org/10.2514/6.2023-3489.vidIn this paper we present recent updates to the Modified Marrone-Treanor thermochemical nonequilibrium model for five-species air, originally developed for computational fluid dynamics calculations of hypersonic flows. The updated (2023) version of the chemistry model used here employs new high-fidelity kinetic rate data for all air reactions (including oxygen/nitrogen/nitric oxide dissociation and Zeldovich exchange reactions) derived from quasi-classical trajectory calculations on \\emphab initio potential energy surfaces. We first verify the updated chemistry model against first-principles Direct Molecular Simulations by studying nonequilibrium reacting air mixtures in space-homogeneous heat baths representative of high-temperature post-shock conditions. Once validated in these simple scenarios, we employ the model in larger-scale computational fluid dynamics studies of hypersonic flow around a geometry representing a generic flight vehicle. There we compare the Modified Marrone-Treanor predictions against the standard nonequilibrium model by Park. This research demonstrates how complex nonequilibrium chemistry induced by hypersonic flight can be incorporated into accurate and efficient models for large-scale computational fluid dynamics simulations.\n
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\n \n\n \n \n Riley, Z. B.; Perez, R.; and Brouwer, K. R.\n\n\n \n \n \n \n Design of Aerothermoelastic Experiments in the AFRL Mach 6 High Reynolds Number Facility.\n \n \n \n\n\n \n\n\n\n In AIAA SCITECH 2023 Forum, 2023. AIAA Paper 2023-0948\n _eprint: https://arc.aiaa.org/doi/pdf/10.2514/6.2023-0948\n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@inproceedings{riley2023,\n\ttitle = {Design of {Aerothermoelastic} {Experiments} in the {AFRL} {Mach} 6 {High} {Reynolds} {Number} {Facility}},\n\tdoi = {10.2514/6.2023-0948},\n\tabstract = {View Video Presentation: https://doi.org/10.2514/6.2023-0948.vidAn experiment was recently conducted in the Air Force Research Laboratory Mach 6 High Reynolds Number Facility exploring the aerothermoelastic response of metallic panels with thicknesses of 381, 508, and 635 μm. Simultaneous, full-field measurements of the panel response were made using stereo digital image correlation, an infrared camera, and a shadowgraph system. Each panel was also instrumented with strain gages and thermocouples. Aeroelastic simulations were carried out to identify the freestream conditions and loading required to exhibit large-amplitude, oscillatory response. Key features of the model design including; an increased length, a pressurized and controllable cavity, and angle of attack variation made it possible to observe panel flutter. Sustained and repeatable large-amplitude oscillations were observed for each panel thickness at different freestream conditions.},\n\turldate = {2023-08-03},\n\tbooktitle = {{AIAA} {SCITECH} 2023 {Forum}},\n\tpublisher = {AIAA Paper 2023-0948},\n\tauthor = {Riley, Zachary B. and Perez, Ricardo and Brouwer, Kirk R.},\n\tyear = {2023},\n\tnote = {\\_eprint: https://arc.aiaa.org/doi/pdf/10.2514/6.2023-0948},\n}\n\n\n\n
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\n View Video Presentation: https://doi.org/10.2514/6.2023-0948.vidAn experiment was recently conducted in the Air Force Research Laboratory Mach 6 High Reynolds Number Facility exploring the aerothermoelastic response of metallic panels with thicknesses of 381, 508, and 635 μm. Simultaneous, full-field measurements of the panel response were made using stereo digital image correlation, an infrared camera, and a shadowgraph system. Each panel was also instrumented with strain gages and thermocouples. Aeroelastic simulations were carried out to identify the freestream conditions and loading required to exhibit large-amplitude, oscillatory response. Key features of the model design including; an increased length, a pressurized and controllable cavity, and angle of attack variation made it possible to observe panel flutter. Sustained and repeatable large-amplitude oscillations were observed for each panel thickness at different freestream conditions.\n
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\n \n\n \n \n Tumuklu, O.; and Hanquist, K. M.\n\n\n \n \n \n \n Unsteadiness of hypersonic flows over a double wedge.\n \n \n \n\n\n \n\n\n\n In AIAA SCITECH 2023 Forum, 2023. AIAA Paper 2023-0860\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n\n\n\n
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@inproceedings{tumuklu2023a,\n\ttitle = {Unsteadiness of hypersonic flows over a double wedge},\n\tdoi = {10.2514/6.2023-0860},\n\tbooktitle = {{AIAA} {SCITECH} 2023 {Forum}},\n\tpublisher = {AIAA Paper 2023-0860},\n\tauthor = {Tumuklu, Ozgur and Hanquist, Kyle M.},\n\tyear = {2023},\n\tkeywords = {own},\n}\n\n\n\n
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\n \n\n \n \n Liza, M. E.; Tumuklu, O.; and Hanquist, K. M.\n\n\n \n \n \n \n Nonequilibrium Effects on Aero-Optics in Hypersonic Flows.\n \n \n \n\n\n \n\n\n\n In AIAA AVIATION, 2023. AIAA Paper 2023-3736\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n\n\n\n
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@inproceedings{liza2023,\n\ttitle = {Nonequilibrium {Effects} on {Aero}-{Optics} in {Hypersonic} {Flows}},\n\tdoi = {10.2514/6.2023-3736},\n\tbooktitle = {{AIAA} {AVIATION}},\n\tpublisher = {AIAA Paper 2023-3736},\n\tauthor = {Liza, Martin E. and Tumuklu, Ozgur and Hanquist, Kyle M.},\n\tyear = {2023},\n\tkeywords = {own},\n}\n\n\n\n
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\n \n\n \n \n Oveissi, P.; Trivedi, A.; Goel, A.; Tumuklu, O.; Hanquist, K. M.; Farahmandi, A.; and Philbrick, D.\n\n\n \n \n \n \n Learning-based Adaptive Thrust Regulation of Solid Fuel Ramjet.\n \n \n \n\n\n \n\n\n\n In AIAA SCITECH 2023 Forum, 2023. AIAA Paper 2023-2533\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n\n\n\n
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@inproceedings{oveissi2023,\n\ttitle = {Learning-based {Adaptive} {Thrust} {Regulation} of {Solid} {Fuel} {Ramjet}},\n\tdoi = {10.2514/6.2023-2533},\n\tbooktitle = {{AIAA} {SCITECH} 2023 {Forum}},\n\tpublisher = {AIAA Paper 2023-2533},\n\tauthor = {Oveissi, Parham and Trivedi, Arjun and Goel, Ankit and Tumuklu, Ozgur and Hanquist, Kyle M. and Farahmandi, Alireza and Philbrick, Douglas},\n\tyear = {2023},\n\tkeywords = {own},\n}\n\n\n\n
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\n \n\n \n \n Hanquist, K. M.\n\n\n \n \n \n \n Importance of Modeling to Hypersonic Flight.\n \n \n \n\n\n \n\n\n\n 2023.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n\n\n\n
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@misc{hanquist2023,\n\taddress = {Program in Applied Math, University of Arizona},\n\ttype = {Invited {Seminar}},\n\ttitle = {Importance of {Modeling} to {Hypersonic} {Flight}},\n\tauthor = {Hanquist, Kyle M.},\n\tyear = {2023},\n\tkeywords = {invited, own},\n}\n\n\n\n
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\n \n\n \n \n Wang, G.; Daniel, K.; Lynch, K. P.; Guildenbecher, D. R.; and Mazumdar, Y. C.\n\n\n \n \n \n \n High Temperature Gladstone-Dale Coefficient Measurements in a Free-Piston Shock Tube.\n \n \n \n\n\n \n\n\n\n In AIAA SCITECH 2023 Forum, 2023. AIAA Paper 2023-0225\n \n\n\n\n
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@inproceedings{wang2023,\n\ttitle = {High {Temperature} {Gladstone}-{Dale} {Coefficient} {Measurements} in a {Free}-{Piston} {Shock} {Tube}},\n\tdoi = {10.2514/6.2023-0225},\n\turldate = {2023-01-27},\n\tbooktitle = {{AIAA} {SCITECH} 2023 {Forum}},\n\tpublisher = {AIAA Paper 2023-0225},\n\tauthor = {Wang, Gwendolyn and Daniel, Kyle and Lynch, Kyle P. and Guildenbecher, Daniel R. and Mazumdar, Yi C.},\n\tyear = {2023},\n}\n\n\n\n
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\n \n\n \n \n Tumuklu, O.; Bellan, J. R.; and Hanquist, K. M.\n\n\n \n \n \n \n Development of a hybrid particle-continuum solver for studying pluma expansion into rarefied flows.\n \n \n \n\n\n \n\n\n\n In AIAA SCITECH 2023 Forum, 2023. AIAA Paper 2023-0073\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n\n\n\n
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@inproceedings{tumuklu2023,\n\ttitle = {Development of a hybrid particle-continuum solver for studying pluma expansion into rarefied flows},\n\tdoi = {10.2514/6.2023-0073},\n\tbooktitle = {{AIAA} {SCITECH} 2023 {Forum}},\n\tpublisher = {AIAA Paper 2023-0073},\n\tauthor = {Tumuklu, Ozgur and Bellan, Josette R. and Hanquist, Kyle M.},\n\tyear = {2023},\n\tkeywords = {own},\n}\n\n\n\n
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\n \n\n \n \n Nastac, G.; Tramel, R. W.; and Nielsen, E. J.\n\n\n \n \n \n \n \n Improved Heat Transfer Prediction for High-Speed Flows over Blunt Bodies using Adaptive Mixed-Element Unstructured Grids.\n \n \n \n \n\n\n \n\n\n\n In AIAA SCITECH 2022 Forum, San Diego, CA & Virtual, January 2022. American Institute of Aeronautics and Astronautics\n \n\n\n\n
\n\n\n\n \n \n \"ImprovedPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@inproceedings{nastac_improved_2022,\n\taddress = {San Diego, CA \\& Virtual},\n\ttitle = {Improved {Heat} {Transfer} {Prediction} for {High}-{Speed} {Flows} over {Blunt} {Bodies} using {Adaptive} {Mixed}-{Element} {Unstructured} {Grids}},\n\tisbn = {978-1-62410-631-6},\n\turl = {https://arc.aiaa.org/doi/10.2514/6.2022-0111},\n\tdoi = {10.2514/6.2022-0111},\n\tlanguage = {en},\n\turldate = {2025-03-04},\n\tbooktitle = {{AIAA} {SCITECH} 2022 {Forum}},\n\tpublisher = {American Institute of Aeronautics and Astronautics},\n\tauthor = {Nastac, Gabriel and Tramel, Robert W. and Nielsen, Eric J.},\n\tmonth = jan,\n\tyear = {2022},\n}\n\n\n\n
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\n \n\n \n \n \n\n\n \n \n \n \n \n Electron Payload User's Guide.\n \n \n \n \n\n\n \n\n\n\n November 2022.\n \n\n\n\n
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@misc{electron2022,\n\ttitle = {Electron {Payload} {User}'s {Guide}},\n\turl = {https://www.rocketlabusa.com/assets/Uploads/Electron-Payload-User-Guide-7.0.pdf},\n\tmonth = nov,\n\tyear = {2022},\n}\n\n\n\n
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\n\n\n\n \n \n \"VulcanPaper\n  \n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@misc{vulcan2022,\n\ttitle = {Vulcan {Centaur}},\n\turl = {https://www.ulalaunch.com/docs/default-source/rockets/vulcancentaur.pdf?sfvrsn=10d7f58f_2},\n\tjournal = {Vulcan Centaur},\n\tyear = {2022},\n}\n\n\n\n
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\n \n\n \n \n Miller, N. E.; Lynch, K. P.; Gordeyev, S.; Guildenbecher, D. R.; Duan, L.; and Wagnild, R. M.\n\n\n \n \n \n \n \n Aero-optical distortions of turbulent boundary layers: Hypersonic DNS.\n \n \n \n \n\n\n \n\n\n\n In AIAA SCITECH 2022 forum, Reston, Virginia, January 2022. American Institute of Aeronautics and Astronautics\n \n\n\n\n
\n\n\n\n \n \n \"Aero-opticalPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@inproceedings{Miller2022,\n\taddress = {Reston, Virginia},\n\ttitle = {Aero-optical distortions of turbulent boundary layers: {Hypersonic} {DNS}},\n\tisbn = {978-1-62410-631-6},\n\turl = {https://arc.aiaa.org/doi/10.2514/6.2022-0056},\n\tdoi = {10.2514/6.2022-0056},\n\tbooktitle = {{AIAA} {SCITECH} 2022 forum},\n\tpublisher = {American Institute of Aeronautics and Astronautics},\n\tauthor = {Miller, Nathan E. and Lynch, Kyle P. and Gordeyev, Stanislav and Guildenbecher, Daniel R. and Duan, Lian and Wagnild, Ross M.},\n\tmonth = jan,\n\tyear = {2022},\n}\n\n\n\n
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\n \n\n \n \n Needels, J. T.; Düzel, Ü.; Hanquist, K. M.; and Alonso, J. J.\n\n\n \n \n \n \n Sensitivity Analysis of Gas-Surface Modeling in Nonequilibrium Flows.\n \n \n \n\n\n \n\n\n\n In AIAA SCITECH 2022 Forum, 2022. AIAA Paper 2022-1636\n \n\n\n\n
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@inproceedings{needels2022,\n\ttitle = {Sensitivity {Analysis} of {Gas}-{Surface} {Modeling} in {Nonequilibrium} {Flows}},\n\tdoi = {10.2514/6.2022-1636},\n\tbooktitle = {{AIAA} {SCITECH} 2022 {Forum}},\n\tpublisher = {AIAA Paper 2022-1636},\n\tauthor = {Needels, Jacob T. and Düzel, Ümran and Hanquist, Kyle M. and Alonso, Juan J.},\n\tyear = {2022},\n\tkeywords = {own},\n}\n\n\n\n
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\n \n\n \n \n Bojan, G. K.; Dutton, J. C.; and Elliott, G. S.\n\n\n \n \n \n \n Fluid/Structure Interaction of Cantilevered Plate in Supersonic Separated Flow.\n \n \n \n\n\n \n\n\n\n AIAA Journal, 60(12): 6726–6738. 2022.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{bojan2022,\n\ttitle = {Fluid/{Structure} {Interaction} of {Cantilevered} {Plate} in {Supersonic} {Separated} {Flow}},\n\tvolume = {60},\n\tissn = {0001-1452},\n\tdoi = {10.2514/1.J061883},\n\tabstract = {The fluid-structure interaction of a cantilevered plate geometry in Mach 2 flow was studied experimentally to assess the effects of structural compliance on the surrounding flowfield. The test geometry, representative of a compliant control surface, consists of an overhanging plate that extends past the edge of a backward-facing step to create a separated region in the flow. This allowed for the study of recirculation effects and unsteady pressure forcing on the cantilevered plate without shock/boundary-layer interactions that would be present if the plate were inclined to the flow. Rigid and compliant test articles were studied to capture the fluid response with and without structural deformation. Schlieren photography and particle image velocimetry showed that under the unsteady conditions during startup of the wind tunnel the flexible plate exhibited a highly dynamic oscillatory response with frequencies similar to its natural vibration response. Under steady, started supersonic flow conditions, the flexible cantilever exhibited smaller oscillations around a mean deflection of two plate thicknesses. Oil flow visualization revealed nontrivial three-dimensionality of the test section flowfield. Modal decomposition of stereo digital image correlation measurements demonstrated that the distinct frequencies present in the flexible plate’s response consistently correspond to the same mode shapes.},\n\tnumber = {12},\n\turldate = {2024-06-18},\n\tjournal = {AIAA Journal},\n\tauthor = {Bojan, Griffin K. and Dutton, J. Craig and Elliott, Gregory S.},\n\tyear = {2022},\n\tpages = {6726--6738},\n}\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n
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\n The fluid-structure interaction of a cantilevered plate geometry in Mach 2 flow was studied experimentally to assess the effects of structural compliance on the surrounding flowfield. The test geometry, representative of a compliant control surface, consists of an overhanging plate that extends past the edge of a backward-facing step to create a separated region in the flow. This allowed for the study of recirculation effects and unsteady pressure forcing on the cantilevered plate without shock/boundary-layer interactions that would be present if the plate were inclined to the flow. Rigid and compliant test articles were studied to capture the fluid response with and without structural deformation. Schlieren photography and particle image velocimetry showed that under the unsteady conditions during startup of the wind tunnel the flexible plate exhibited a highly dynamic oscillatory response with frequencies similar to its natural vibration response. Under steady, started supersonic flow conditions, the flexible cantilever exhibited smaller oscillations around a mean deflection of two plate thicknesses. Oil flow visualization revealed nontrivial three-dimensionality of the test section flowfield. Modal decomposition of stereo digital image correlation measurements demonstrated that the distinct frequencies present in the flexible plate’s response consistently correspond to the same mode shapes.\n
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\n \n\n \n \n Kumar Reddy Sirigiri, V.; Yadav Gudiga, V.; Shankar Gattu, U.; Suneesh, G.; and Mohan Buddaraju, K.\n\n\n \n \n \n \n A review on Johnson Cook material model.\n \n \n \n\n\n \n\n\n\n Materials Today: Proceedings, 62: 3450–3456. January 2022.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{kumarreddysirigiri2022,\n\tseries = {International {Conference} on {Materials}, {Processing} \\& {Characterization} (13th {ICMPC})},\n\ttitle = {A review on {Johnson} {Cook} material model},\n\tvolume = {62},\n\tdoi = {10.1016/j.matpr.2022.04.279},\n\tabstract = {To design and optimise process parameters in the metal forming industry, it is necessary to have a consistent and realistic representation of material behaviour where strain, strain rate, and temperature have an effect on the material flow stress. This paper examines various approaches that are employed in calculating the Johnson Cook material constants. Split Hopkinson-bar methodology and universal tensile tests were used to determine the material constants related to Johnson Cook material and failure models. These models were used in numerical simulations to facilitate design optimization and reduce experimentation costs. Johnson Cook material models were employed in various simulation software’s like ABAQUS, LS-DYNA, and DEFORM 3D to simulate metal turning, milling, and forming operations.},\n\turldate = {2024-06-12},\n\tjournal = {Materials Today: Proceedings},\n\tauthor = {Kumar Reddy Sirigiri, Vasu and Yadav Gudiga, Vinith and Shankar Gattu, Uday and Suneesh, G. and Mohan Buddaraju, Krishna},\n\tmonth = jan,\n\tyear = {2022},\n\tkeywords = {Deformation, Identification method, Johnson Cook failure model, Johnson Cook model, Numerical Simulation},\n\tpages = {3450--3456},\n}\n\n\n\n
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\n To design and optimise process parameters in the metal forming industry, it is necessary to have a consistent and realistic representation of material behaviour where strain, strain rate, and temperature have an effect on the material flow stress. This paper examines various approaches that are employed in calculating the Johnson Cook material constants. Split Hopkinson-bar methodology and universal tensile tests were used to determine the material constants related to Johnson Cook material and failure models. These models were used in numerical simulations to facilitate design optimization and reduce experimentation costs. Johnson Cook material models were employed in various simulation software’s like ABAQUS, LS-DYNA, and DEFORM 3D to simulate metal turning, milling, and forming operations.\n
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\n \n\n \n \n Vatansever, D.; Nuwal, N.; and Levin, D. A.\n\n\n \n \n \n \n \n A Parametric Study for Kinetic Modeling of Emissive Sheaths Using Electrostatic Particle-in-Cell Method.\n \n \n \n \n\n\n \n\n\n\n In AIAA AVIATION 2022 Forum, 2022. AIAA Paper 2022-3361\n \n\n\n\n
\n\n\n\n \n \n \"APaper\n  \n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{vatansever2022,\n\ttitle = {A {Parametric} {Study} for {Kinetic} {Modeling} of {Emissive} {Sheaths} {Using} {Electrostatic} {Particle}-in-{Cell} {Method}},\n\turl = {https://arc.aiaa.org/doi/abs/10.2514/6.2022-3361},\n\tabstract = {View Video Presentation: https://doi.org/10.2514/6.2022-3361.vidA one-dimensional collisionless space charge limited (SCL) sheath is solved by using electro-static Particle-in-cell (PIC) method. We conduct a parametric study with different plasma conditions to understand the emissive nature of SCL sheaths and electron transpiration cooling (ETC) of the surface in high-speed flows. It is seen that potential profile along a 1-D plasma is sensitive to changes of the ion to electron mass ratio (mi/me), the electron emission temperature (Temit), the number of emitted particles (Nemit) and length of the plasma slab (L). We observe that the emitted electrons with higher energies escape the SCL sheath more easily but others are trapped within the SCL sheath. The thermionic emission from the emitting wall increases with increased ion to electron mass ratio and electron emission temperature but becomes less when the length of plasma is increased.},\n\turldate = {2024-04-12},\n\tbooktitle = {{AIAA} {AVIATION} 2022 {Forum}},\n\tpublisher = {AIAA Paper 2022-3361},\n\tauthor = {Vatansever, Davut and Nuwal, Nakul and Levin, Deborah A.},\n\tyear = {2022},\n}\n\n\n\n
\n
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\n View Video Presentation: https://doi.org/10.2514/6.2022-3361.vidA one-dimensional collisionless space charge limited (SCL) sheath is solved by using electro-static Particle-in-cell (PIC) method. We conduct a parametric study with different plasma conditions to understand the emissive nature of SCL sheaths and electron transpiration cooling (ETC) of the surface in high-speed flows. It is seen that potential profile along a 1-D plasma is sensitive to changes of the ion to electron mass ratio (mi/me), the electron emission temperature (Temit), the number of emitted particles (Nemit) and length of the plasma slab (L). We observe that the emitted electrons with higher energies escape the SCL sheath more easily but others are trapped within the SCL sheath. The thermionic emission from the emitting wall increases with increased ion to electron mass ratio and electron emission temperature but becomes less when the length of plasma is increased.\n
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\n \n\n \n \n Beving, L. P.; Hopkins, M. M.; and Baalrud, S. D.\n\n\n \n \n \n \n How sheath properties change with gas pressure: modeling and simulation.\n \n \n \n\n\n \n\n\n\n Plasma Sources Science and Technology, 31(8): 084009. August 2022.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{beving2022,\n\ttitle = {How sheath properties change with gas pressure: modeling and simulation},\n\tvolume = {31},\n\tissn = {0963-0252},\n\tshorttitle = {How sheath properties change with gas pressure},\n\tdoi = {10.1088/1361-6595/ac85d7},\n\tabstract = {Particle-in-cell simulations are used to study how neutral pressure influences plasma properties at the sheath edge. The high rate of ion–neutral collisions at pressures above several mTorr are found to cause a decrease in the ion velocity at the sheath edge (collisional Bohm criterion), a decrease in the edge-to-center density ratio (h l factor), and an increase in the sheath width and sheath potential drop. A comparison with existing analytic models generally indicates favorable agreement, but with some distinctions. One is that models for the h l factor need to be made consistent with the collisional Bohm criterion. With this and similar corrections, a comprehensive fluid-based model of the plasma boundary transition is constructed that compares well with the simulation results.},\n\tlanguage = {en},\n\tnumber = {8},\n\turldate = {2024-04-24},\n\tjournal = {Plasma Sources Science and Technology},\n\tauthor = {Beving, L. P. and Hopkins, M. M. and Baalrud, S. D.},\n\tmonth = aug,\n\tyear = {2022},\n\tpages = {084009},\n}\n\n\n\n\n\n\n\n
\n
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\n Particle-in-cell simulations are used to study how neutral pressure influences plasma properties at the sheath edge. The high rate of ion–neutral collisions at pressures above several mTorr are found to cause a decrease in the ion velocity at the sheath edge (collisional Bohm criterion), a decrease in the edge-to-center density ratio (h l factor), and an increase in the sheath width and sheath potential drop. A comparison with existing analytic models generally indicates favorable agreement, but with some distinctions. One is that models for the h l factor need to be made consistent with the collisional Bohm criterion. With this and similar corrections, a comprehensive fluid-based model of the plasma boundary transition is constructed that compares well with the simulation results.\n
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\n \n\n \n \n Munafò, A.; Chiodi, R.; Kumar, S.; Maout, V. L.; Stephani, K. A.; Panerai, F.; Bodony, D. J.; and Panesi, M.\n\n\n \n \n \n \n \n A Multi-Physics Modeling Framework for Inductively Coupled Plasma Wind Tunnels.\n \n \n \n \n\n\n \n\n\n\n In AIAA SCITECH 2022 Forum, 2022. AIAA Paper 2022-2011\n \n\n\n\n
\n\n\n\n \n \n \"APaper\n  \n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{munafo2022,\n\ttitle = {A {Multi}-{Physics} {Modeling} {Framework} for {Inductively} {Coupled} {Plasma} {Wind} {Tunnels}},\n\turl = {https://arc.aiaa.org/doi/abs/10.2514/6.2022-1011},\n\tabstract = {View Video Presentation: https://doi.org/10.2514/6.2022-1011.vidThis work discusses the development of a multi-physics modeling framework for Inductively Coupled Plasma (ICP) wind tunnels. As opposed to a monolithic approach, separate in-house solvers are considered to deal with the different parts of the complete model. The flowfield is modeled using hegel, a finite volume solver for non-equilibrium plasmas. The simulation of the electric field and the thermal Protection System (TPS) material sample is accomplished via a finite element solver and a finite volume solver (flux and pato, respectively). The three tools are coupled using the preCICE library. Results for a two-dimensional axi-symmetric ICP configuration are presented and discussed to illustrate the effectiveness of the proposed coupled approach for modeling ICP discharges along with material response and electromagnetic phenomena.},\n\turldate = {2024-04-24},\n\tbooktitle = {{AIAA} {SCITECH} 2022 {Forum}},\n\tpublisher = {AIAA Paper 2022-2011},\n\tauthor = {Munafò, Alessandro and Chiodi, Robert and Kumar, Sanjeev and Maout, Vincent Le and Stephani, Kelly A. and Panerai, Francesco and Bodony, Daniel J. and Panesi, Marco},\n\tyear = {2022},\n}\n\n\n\n\n\n\n\n\n\n\n\n
\n
\n\n\n
\n View Video Presentation: https://doi.org/10.2514/6.2022-1011.vidThis work discusses the development of a multi-physics modeling framework for Inductively Coupled Plasma (ICP) wind tunnels. As opposed to a monolithic approach, separate in-house solvers are considered to deal with the different parts of the complete model. The flowfield is modeled using hegel, a finite volume solver for non-equilibrium plasmas. The simulation of the electric field and the thermal Protection System (TPS) material sample is accomplished via a finite element solver and a finite volume solver (flux and pato, respectively). The three tools are coupled using the preCICE library. Results for a two-dimensional axi-symmetric ICP configuration are presented and discussed to illustrate the effectiveness of the proposed coupled approach for modeling ICP discharges along with material response and electromagnetic phenomena.\n
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\n \n\n \n \n Tomko, J. A.; Johnson, M. J.; Boris, D. R.; Petrova, T. B.; Walton, S. G.; and Hopkins, P. E.\n\n\n \n \n \n \n Plasma-induced surface cooling.\n \n \n \n\n\n \n\n\n\n Nature Communications, 13(1). May 2022.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{tomko2022,\n\ttitle = {Plasma-induced surface cooling},\n\tvolume = {13},\n\tcopyright = {2022 The Author(s)},\n\tissn = {2041-1723},\n\tdoi = {10.1038/s41467-022-30170-5},\n\tabstract = {Plasmas are an indispensable materials engineering tool due to their unique ability to deliver a flux of species and energy to a surface. This energy flux serves to heat the surface out of thermal equilibrium with bulk material, thus enabling local physicochemical processes that can be harnessed for material manipulation. However, to-date, there have been no reports on the direct measurement of the localized, transient thermal response of a material surface exposed to a plasma. Here, we use time-resolved optical thermometry in-situ to show that the energy flux from a pulsed plasma serves to both heat and transiently cool the material surface. To identify potential mechanisms for this ‘plasma cooling,’ we employ time-resolved plasma diagnostics to correlate the photon and charged particle flux with the thermal response of the material. The results indicate photon-stimulated desorption of adsorbates from the surface is the most likely mechanism responsible for this plasma cooling.},\n\tlanguage = {en},\n\tnumber = {1},\n\turldate = {2024-04-10},\n\tjournal = {Nature Communications},\n\tauthor = {Tomko, John A. and Johnson, Michael J. and Boris, David R. and Petrova, Tzvetelina B. and Walton, Scott G. and Hopkins, Patrick E.},\n\tmonth = may,\n\tyear = {2022},\n\tkeywords = {Applied physics, Characterization and analytical techniques, Materials for energy and catalysis, Plasma physics},\n}\n\n\n\n\n\n\n\n
\n
\n\n\n
\n Plasmas are an indispensable materials engineering tool due to their unique ability to deliver a flux of species and energy to a surface. This energy flux serves to heat the surface out of thermal equilibrium with bulk material, thus enabling local physicochemical processes that can be harnessed for material manipulation. However, to-date, there have been no reports on the direct measurement of the localized, transient thermal response of a material surface exposed to a plasma. Here, we use time-resolved optical thermometry in-situ to show that the energy flux from a pulsed plasma serves to both heat and transiently cool the material surface. To identify potential mechanisms for this ‘plasma cooling,’ we employ time-resolved plasma diagnostics to correlate the photon and charged particle flux with the thermal response of the material. The results indicate photon-stimulated desorption of adsorbates from the surface is the most likely mechanism responsible for this plasma cooling.\n
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\n \n\n \n \n Chourdakis, G; Davis, K; Rodenberg, B; Schulte, M; Simonis, F; Uekermann, B; Abrams, G; Bungartz, H.; Cheung Yau, L; Desai, I; Eder, K; Hertrich, R; Lindner, F; Rusch, A; Sashko, D; Schneider, D; Totounferoush, A; Volland, D; Vollmer, P; and Koseomur, O.\n\n\n \n \n \n \n preCICE v2: A sustainable and user-friendly coupling library.\n \n \n \n\n\n \n\n\n\n Open Research Europe, 2(51). 2022.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{chourdakis2022,\n\ttitle = {{preCICE} v2: {A} sustainable and user-friendly coupling library},\n\tvolume = {2},\n\tdoi = {10.12688/openreseurope.14445.2},\n\tnumber = {51},\n\tjournal = {Open Research Europe},\n\tauthor = {Chourdakis, G and Davis, K and Rodenberg, B and Schulte, M and Simonis, F and Uekermann, B and Abrams, G and Bungartz, HJ and Cheung Yau, L and Desai, I and Eder, K and Hertrich, R and Lindner, F and Rusch, A and Sashko, D and Schneider, D and Totounferoush, A and Volland, D and Vollmer, P and Koseomur, OZ},\n\tyear = {2022},\n}\n\n\n\n
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\n \n\n \n \n Schmidt, J. D.; Nichols, J. T.; Dietz, C. J.; Askins, P.; Ford, K. F.; Perry, A.; Smith, W. T.; and Martin, A.\n\n\n \n \n \n \n Kentucky Re-Entry Universal Payload System (KRUPS): Overview of flight test via high-altitude balloon.\n \n \n \n\n\n \n\n\n\n In AIAA AVIATION 2022 Forum, 2022. AIAA Paper 2022-3729\n _eprint: https://arc.aiaa.org/doi/pdf/10.2514/6.2022-3729\n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{schmidt_kentucky_2022,\n\ttitle = {Kentucky {Re}-{Entry} {Universal} {Payload} {System} ({KRUPS}): {Overview} of flight test via high-altitude balloon},\n\tshorttitle = {Kentucky {Re}-{Entry} {Universal} {Payload} {System} ({KRUPS})},\n\tdoi = {10.2514/6.2022-3729},\n\tabstract = {View Video Presentation: https://doi.org/10.2514/6.2022-3729.vidThe Kentucky Re-entry Universal Payload System (KRUPS) is a small re-entry capsule designed as a technology testbed. For its first incarnation, KRUPS has been designed to test Thermal Protection System (TPS) material and instrumentation. TPS are used to protect spacecraft, and its payload, from the extreme conditions of planetary entry. KRUPS has been developed at the University of Kentucky over the past 6 years. This specific launch aimed to produce system verification, software implementation, and launch qualifications, using an atmospheric balloon platform. The capsule released from the balloon in this experiment, was designed to transmit data using the Iridium satellite network. Recovery of the capsule was planned, using a parachute that aimed at preventing a crash landing and thus protecting the internal components. The capsule was activated and ejected as planned. Thermal measurements of the TPS were received by the capsule as it returned to Earth. This satisfied the main objective of the flight. However, the capsule did not have a successful parachute deployment, due to a timing issue. Therefore, the capsule was not able to be recovered in one piece. The thermal data measured during the descent of this capsule demonstrated the insulative properties of the TPS.},\n\turldate = {2023-10-30},\n\tbooktitle = {{AIAA} {AVIATION} 2022 {Forum}},\n\tpublisher = {AIAA Paper 2022-3729},\n\tauthor = {Schmidt, John D. and Nichols, J. T. and Dietz, Collin J. and Askins, Page and Ford, Kirsten F. and Perry, Andrew and Smith, William T. and Martin, Alexandre},\n\tyear = {2022},\n\tnote = {\\_eprint: https://arc.aiaa.org/doi/pdf/10.2514/6.2022-3729},\n}\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n
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\n View Video Presentation: https://doi.org/10.2514/6.2022-3729.vidThe Kentucky Re-entry Universal Payload System (KRUPS) is a small re-entry capsule designed as a technology testbed. For its first incarnation, KRUPS has been designed to test Thermal Protection System (TPS) material and instrumentation. TPS are used to protect spacecraft, and its payload, from the extreme conditions of planetary entry. KRUPS has been developed at the University of Kentucky over the past 6 years. This specific launch aimed to produce system verification, software implementation, and launch qualifications, using an atmospheric balloon platform. The capsule released from the balloon in this experiment, was designed to transmit data using the Iridium satellite network. Recovery of the capsule was planned, using a parachute that aimed at preventing a crash landing and thus protecting the internal components. The capsule was activated and ejected as planned. Thermal measurements of the TPS were received by the capsule as it returned to Earth. This satisfied the main objective of the flight. However, the capsule did not have a successful parachute deployment, due to a timing issue. Therefore, the capsule was not able to be recovered in one piece. The thermal data measured during the descent of this capsule demonstrated the insulative properties of the TPS.\n
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\n \n\n \n \n \n\n\n \n \n \n \n \n Need for hypersonics workforce development ‘an issue of national security’.\n \n \n \n \n\n\n \n\n\n\n Hypersonics Systems Initiative - University of Notre Dame. 2022.\n \n\n\n\n
\n\n\n\n \n \n \"NeedPaper\n  \n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{nd2022,\n\ttitle = {Need for hypersonics workforce development ‘an issue of national security’},\n\turl = {https://hypersonics.nd.edu/news-events/news/need-for-hypersonics-workforce-development-an-issue-of-national-security/},\n\tjournal = {Hypersonics Systems Initiative - University of Notre Dame},\n\tyear = {2022},\n}\n\n\n\n
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\n \n\n \n \n Streicher, J. W.; Krish, A.; and Hanson, R. K.\n\n\n \n \n \n \n \n High-temperature vibrational relaxation and decomposition of shock-heated nitric oxide: II. Nitrogen dilution from 1900 to 8200 K.\n \n \n \n \n\n\n \n\n\n\n Physics of Fluids, 34(11): 116123. November 2022.\n \n\n\n\n
\n\n\n\n \n \n \"High-temperaturePaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{streicher2022,\n\ttitle = {High-temperature vibrational relaxation and decomposition of shock-heated nitric oxide: {II}. {Nitrogen} dilution from 1900 to 8200 {K}},\n\tvolume = {34},\n\tissn = {1070-6631},\n\tshorttitle = {High-temperature vibrational relaxation and decomposition of shock-heated nitric oxide},\n\turl = {https://doi.org/10.1063/5.0122787},\n\tdoi = {10.1063/5.0122787},\n\tabstract = {This work investigates the high-temperature vibrational relaxation and decomposition of nitric oxide (NO) diluted in nitrogen (N2) to target the NO–N2 rates relevant to high-temperature air, thereby building off the argon (Ar) experiments investigated in Part I. [J. W. Streicher et al., “High-temperature vibrational relaxation and decomposition of shock-heated nitric oxide. I. Argon dilution from 2200 to 8700 K,” Phys. Fluids 34, 116122 (2022)] Again, two continuous-wave ultraviolet laser diagnostics were used to obtain quantum-state-specific time histories of NO in high-temperature shock-tube experiments, including absorbance (α) in the ground vibrational state of NO, translational/rotational temperature (Ttr), and number density of NO (nNO). The experiments probed mixtures of 2\\% and 0.4\\% NO diluted in either pure N2 (NO/N2) or an equal parts N2/Ar mixture (NO/N2/Ar). The NO/N2 experiments spanned initial post-reflected-shock conditions from 1900–7000 K and 0.05–1.14 atm, while the NO/N2/Ar experiments spanned from 1900–8200 K and 0.11–1.52 atm. This work leveraged two vibrational relaxation times from Part I (τVTNO−Ar and τVTNO−NO) and extended measurements to include the vibrational–translational and vibrational–vibrational relaxation times with N2 (τVTNO−N2 and τVVNO−N2). Similarly, this work leveraged the four rate coefficients from Part I (kdNO−Ar, kdNO−NO, kfN2O, and kzNO−O) and extended measurements to include NO dissociation with N2 (kdNO−N2). A few studies have directly inferred these rates from experiments, and the current data differ from common model values. In particular, τVTNO−N2 differs slightly from the Millikan and White correlation, τVVNO−N2 is four times slower than Taylor et al.'s inference, and kdNO−N2 is four times slower than the Park two-temperature model. The unique experimental measurements and dilution in N2 in this study significantly improve the understanding of the vibrational relaxation and decomposition of NO in high-temperature air.},\n\tnumber = {11},\n\turldate = {2023-08-10},\n\tjournal = {Physics of Fluids},\n\tauthor = {Streicher, Jesse W. and Krish, Ajay and Hanson, Ronald K.},\n\tmonth = nov,\n\tyear = {2022},\n\tpages = {116123},\n}\n\n\n\n
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\n This work investigates the high-temperature vibrational relaxation and decomposition of nitric oxide (NO) diluted in nitrogen (N2) to target the NO–N2 rates relevant to high-temperature air, thereby building off the argon (Ar) experiments investigated in Part I. [J. W. Streicher et al., “High-temperature vibrational relaxation and decomposition of shock-heated nitric oxide. I. Argon dilution from 2200 to 8700 K,” Phys. Fluids 34, 116122 (2022)] Again, two continuous-wave ultraviolet laser diagnostics were used to obtain quantum-state-specific time histories of NO in high-temperature shock-tube experiments, including absorbance (α) in the ground vibrational state of NO, translational/rotational temperature (Ttr), and number density of NO (nNO). The experiments probed mixtures of 2% and 0.4% NO diluted in either pure N2 (NO/N2) or an equal parts N2/Ar mixture (NO/N2/Ar). The NO/N2 experiments spanned initial post-reflected-shock conditions from 1900–7000 K and 0.05–1.14 atm, while the NO/N2/Ar experiments spanned from 1900–8200 K and 0.11–1.52 atm. This work leveraged two vibrational relaxation times from Part I (τVTNO−Ar and τVTNO−NO) and extended measurements to include the vibrational–translational and vibrational–vibrational relaxation times with N2 (τVTNO−N2 and τVVNO−N2). Similarly, this work leveraged the four rate coefficients from Part I (kdNO−Ar, kdNO−NO, kfN2O, and kzNO−O) and extended measurements to include NO dissociation with N2 (kdNO−N2). A few studies have directly inferred these rates from experiments, and the current data differ from common model values. In particular, τVTNO−N2 differs slightly from the Millikan and White correlation, τVVNO−N2 is four times slower than Taylor et al.'s inference, and kdNO−N2 is four times slower than the Park two-temperature model. The unique experimental measurements and dilution in N2 in this study significantly improve the understanding of the vibrational relaxation and decomposition of NO in high-temperature air.\n
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\n \n\n \n \n Bearden, K. P.; Padilla, V. E.; Taubert, L.; and Craig, S. A.\n\n\n \n \n \n \n \n Calibration and performance characterization of a Mach 5 Ludwieg tube.\n \n \n \n \n\n\n \n\n\n\n Review of Scientific Instruments, 93(8): 085104. August 2022.\n \n\n\n\n
\n\n\n\n \n \n \"CalibrationPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{bearden2022,\n\ttitle = {Calibration and performance characterization of a {Mach} 5 {Ludwieg} tube},\n\tvolume = {93},\n\tissn = {0034-6748},\n\turl = {https://doi.org/10.1063/5.0093052},\n\tdoi = {10.1063/5.0093052},\n\tabstract = {Calibration, commissioning, and design features of a new Mach 5 Ludwieg Tube wind tunnel at the University of Arizona are discussed. Mach number uniformity and free-stream noise levels are measured using a Pitot rake at a range of unit Reynolds numbers and at multiple spanwise and streamwise positions. The wind tunnel is shown to have a free-stream Mach number of 4.82 with maximum variance less than 0.8\\% (and less than 0.5\\% at most streamwise positions). The average free-stream acoustic noise level in the core (based on Pitot pressure) is shown to be less than 1.2\\% at an intermediate Reynolds number with some regions dropping locally below 1.0\\%. The core flow region is measured to be 282.4 mm (11.1 in.) in diameter at the nozzle exit.},\n\tnumber = {8},\n\turldate = {2023-08-08},\n\tjournal = {Review of Scientific Instruments},\n\tauthor = {Bearden, Kyle P. and Padilla, Victor E. and Taubert, Lutz and Craig, Stuart A.},\n\tmonth = aug,\n\tyear = {2022},\n\tpages = {085104},\n}\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n
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\n Calibration, commissioning, and design features of a new Mach 5 Ludwieg Tube wind tunnel at the University of Arizona are discussed. Mach number uniformity and free-stream noise levels are measured using a Pitot rake at a range of unit Reynolds numbers and at multiple spanwise and streamwise positions. The wind tunnel is shown to have a free-stream Mach number of 4.82 with maximum variance less than 0.8% (and less than 0.5% at most streamwise positions). The average free-stream acoustic noise level in the core (based on Pitot pressure) is shown to be less than 1.2% at an intermediate Reynolds number with some regions dropping locally below 1.0%. The core flow region is measured to be 282.4 mm (11.1 in.) in diameter at the nozzle exit.\n
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\n \n\n \n \n Gould, J.\n\n\n \n \n \n \n \n Pentagon’s fuel prices rose $3 billion amid inflationary pressures.\n \n \n \n \n\n\n \n\n\n\n April 2022.\n Section: Congress\n\n\n\n
\n\n\n\n \n \n \"Pentagon’sPaper\n  \n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@misc{gould2022,\n\ttitle = {Pentagon’s fuel prices rose \\$3 billion amid inflationary pressures},\n\turl = {https://www.defensenews.com/pentagon/2022/04/27/pentagons-fuel-prices-rose-3b-amid-inflationary-pressures/},\n\tabstract = {Spiking fuel prices will cost the Pentagon \\$3 billion more than expected, and it will have to go to Congress for more money, a senior official said in congressional testimony on Wednesday.},\n\tlanguage = {en},\n\turldate = {2023-06-28},\n\tjournal = {Defense News},\n\tauthor = {Gould, Joe},\n\tmonth = apr,\n\tyear = {2022},\n\tnote = {Section: Congress},\n}\n\n\n\n
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\n Spiking fuel prices will cost the Pentagon $3 billion more than expected, and it will have to go to Congress for more money, a senior official said in congressional testimony on Wednesday.\n
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\n \n\n \n \n Sawicki, P.; Chaudhry, R. S.; and Boyd, I. D.\n\n\n \n \n \n \n Influence of Chemical Kinetics Models on Plasma Generation in Hypersonic Flight.\n \n \n \n\n\n \n\n\n\n AIAA Journal, 60(1): 31–40. August 2022.\n Publisher: AIAA International\n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{sawicki2022,\n\ttitle = {Influence of {Chemical} {Kinetics} {Models} on {Plasma} {Generation} in {Hypersonic} {Flight}},\n\tvolume = {60},\n\tdoi = {10.2514/1.J060615/ASSET/IMAGES/LARGE/FIGURE11.JPEG},\n\tabstract = {The accuracy and sensitivity of plasma generation predicted by several different chemical kinetics models is investigated in the context of weakly ionized hypersonic flowfields around the Radio Attenuation Measurement (RAM-C) vehicle. A computational fluid dynamics analysis is used to examine 13 independent trajectory points along the RAM-C II flight, and an assessment of the chemistry models is made by comparing results to available flight measurements. The limitations of making such comparisons with the raw flight data are established in detail, including the inherent shortcomings associated with interpolating the flight data to assess a single trajectory point. Two separate geometries are evaluated in this study, as the initial RAM-C geometry was altered during flight after its nose cap was pyrotechnically ejected. The blunter post-ejection geometry generates more electrons in the stagnation region. In general, good agreement is found between each chemistry model and flight data from both the electrostatic probe and reflectometer stations above 56 km. An expected sizable gap exists between the simulations and reflectometer data at lower altitudes. The impact of forward reaction rates, equilibrium constants, and number of species varies considerably based on altitude, velocity, and position along the body.},\n\tnumber = {1},\n\tjournal = {AIAA Journal},\n\tauthor = {Sawicki, Pawel and Chaudhry, Ross S. and Boyd, Iain D.},\n\tmonth = aug,\n\tyear = {2022},\n\tnote = {Publisher: AIAA International},\n\tkeywords = {Angle of Attack, Bow Shock, CFD Analysis, Chemical Kinetics, Flight Data, Flight Testing, Free Molecular Flow, Hypersonic Flight, No Slip Condition, Plasma Diagnostics},\n\tpages = {31--40},\n}\n\n\n\n
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\n The accuracy and sensitivity of plasma generation predicted by several different chemical kinetics models is investigated in the context of weakly ionized hypersonic flowfields around the Radio Attenuation Measurement (RAM-C) vehicle. A computational fluid dynamics analysis is used to examine 13 independent trajectory points along the RAM-C II flight, and an assessment of the chemistry models is made by comparing results to available flight measurements. The limitations of making such comparisons with the raw flight data are established in detail, including the inherent shortcomings associated with interpolating the flight data to assess a single trajectory point. Two separate geometries are evaluated in this study, as the initial RAM-C geometry was altered during flight after its nose cap was pyrotechnically ejected. The blunter post-ejection geometry generates more electrons in the stagnation region. In general, good agreement is found between each chemistry model and flight data from both the electrostatic probe and reflectometer stations above 56 km. An expected sizable gap exists between the simulations and reflectometer data at lower altitudes. The impact of forward reaction rates, equilibrium constants, and number of species varies considerably based on altitude, velocity, and position along the body.\n
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\n \n\n \n \n Castillo Gomez, P.; Gross, A.; Guildenbecher, D. R.; Miller, N. E.; and Lynch, K. P.\n\n\n \n \n \n \n Wall-Modeled Large-Eddy Simulations of Turbulent Mach 3.5, 8, and 14 Boundary Layers - Effect of Mach Number on Aero-Optical Distortions.\n \n \n \n\n\n \n\n\n\n In June 2022. AIAA Paper 2022-2441\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{castillogomez2022,\n\ttitle = {Wall-{Modeled} {Large}-{Eddy} {Simulations} of {Turbulent} {Mach} 3.5, 8, and 14 {Boundary} {Layers} - {Effect} of {Mach} {Number} on {Aero}-{Optical} {Distortions}},\n\tdoi = {10.2514/6.2022-3441},\n\tlanguage = {en},\n\tpublisher = {AIAA Paper 2022-2441},\n\tauthor = {Castillo Gomez, Pedro and Gross, Andreas and Guildenbecher, Daniel R. and Miller, Nathan E. and Lynch, Kyle P.},\n\tmonth = jun,\n\tyear = {2022},\n}\n\n\n\n
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\n \n\n \n \n Castillo, P.; Gross, A.; Miller, N. E.; Guildenbecher, D. R.; and Lynch, K. P.\n\n\n \n \n \n \n Wall-Modeled Large-Eddy Simulations of Mach 8 Turbulent Boundary Layer and Computation of Aero-Optical Distortions.\n \n \n \n\n\n \n\n\n\n In 2022. American Institute of Aeronautics and Astronautics Inc, AIAA\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{castillo2022,\n\ttitle = {Wall-{Modeled} {Large}-{Eddy} {Simulations} of {Mach} 8 {Turbulent} {Boundary} {Layer} and {Computation} of {Aero}-{Optical} {Distortions}},\n\tisbn = {978-1-62410-631-6},\n\tdoi = {10.2514/6.2022-1674},\n\tabstract = {Compressible wall modeled large-eddy simulations of a Mach eight turbulent boundary layer over a flat plate were carried out for the conditions of the Hypersonic Wind Tunnel at Sandia National Laboratories. Overall good agreement of the velocity and temperature profiles is obtained with reference data from a direct numerical simulation and a theoretical relationship. Profiles of the resolved root-mean-square velocity fluctuations are in adequate agreement with the reference data. The refractive index is calculated from the density field and integrated along an expected beam path to calculate the optical path length. Then, by subtracting a bilinear fit of the instantaneous optical path length, the optical path difference is obtained. The computed aero-optical path difference shows a similar dependence on the aperture size as in the literature. The normalized root-mean-square optical path difference from the present wall-modeled large-eddy simulations and a reference direct numerical simulation and experiment are in good agreement. The optical path distortion is slightly above the value predicted by a semi-analytical relationship from the literature. Finally, instantaneous snapshots of the flow are analyzed via proper orthogonal decomposition and the optical path distortion is computed from subsets of the modes. The optical path distortion converges quickly with increasing number of modes which suggests that the main contribution comes from large energetic flow structures.},\n\tpublisher = {American Institute of Aeronautics and Astronautics Inc, AIAA},\n\tauthor = {Castillo, Pedro and Gross, Andreas and Miller, Nathan E. and Guildenbecher, Daniel R. and Lynch, Kyle P.},\n\tyear = {2022},\n}\n\n\n\n
\n
\n\n\n
\n Compressible wall modeled large-eddy simulations of a Mach eight turbulent boundary layer over a flat plate were carried out for the conditions of the Hypersonic Wind Tunnel at Sandia National Laboratories. Overall good agreement of the velocity and temperature profiles is obtained with reference data from a direct numerical simulation and a theoretical relationship. Profiles of the resolved root-mean-square velocity fluctuations are in adequate agreement with the reference data. The refractive index is calculated from the density field and integrated along an expected beam path to calculate the optical path length. Then, by subtracting a bilinear fit of the instantaneous optical path length, the optical path difference is obtained. The computed aero-optical path difference shows a similar dependence on the aperture size as in the literature. The normalized root-mean-square optical path difference from the present wall-modeled large-eddy simulations and a reference direct numerical simulation and experiment are in good agreement. The optical path distortion is slightly above the value predicted by a semi-analytical relationship from the literature. Finally, instantaneous snapshots of the flow are analyzed via proper orthogonal decomposition and the optical path distortion is computed from subsets of the modes. The optical path distortion converges quickly with increasing number of modes which suggests that the main contribution comes from large energetic flow structures.\n
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\n \n\n \n \n Huang, D.; Sadagopan, A.; Düzel, Ü.; and Hanquist, K. M.\n\n\n \n \n \n \n Study of fluid–thermal–structural interaction in high-temperature high-speed flow using multi-fidelity multi-variate surrogates.\n \n \n \n\n\n \n\n\n\n Journal of Fluids and Structures, 113. 2022.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{huang2022,\n\ttitle = {Study of fluid–thermal–structural interaction in high-temperature high-speed flow using multi-fidelity multi-variate surrogates},\n\tvolume = {113},\n\tdoi = {10.1016/j.jfluidstructs.2022.103682},\n\tabstract = {This study investigates the impact of the high-temperature effect, especially the real gas effect and chemical reactions, on hypersonic aerothermodynamic solutions of double cone and double wedge configurations, as well as the fluid–thermal–structural interaction of a double wedge configuration in hypersonic flow. First, a high-temperature computational fluid dynamics (CFD) code was benchmarked and correlated with experimental results, emphasizing the impact of high-temperature effects as well as turbulence modeling on heat flux prediction. Subsequently, the multi-fidelity multi-variate Gaussian process regression (M2GPR ) method for problems with high-dimensional outputs was developed to create an aerothermal surrogate model. The model achieves a balance between model accuracy and computational cost of sample generation, using the combination of a few high-fidelity samples and many low-fidelity samples. The numerical examples show that, using the M2GPR formulation, the required number of high-fidelity samples may be reduced by over 80\\% while maintaining an accuracy comparable to the high-fidelity CFD solvers. In addition, a geodesic-distance-based metric is developed to inform the choice of high-dimensional datasets of different fidelities for the M2GPR surrogate with improved accuracy. Finally, the aerothermal surrogate was applied to study the impact of the high-temperature effect on the aerothermoelastic response of a hypersonic skin panel, emphasizing the necessity of the accurate characterization of the localized heat flux for reasonable assessment of the response of a compliant structure in high-speed high-temperature flowfield.},\n\tjournal = {Journal of Fluids and Structures},\n\tauthor = {Huang, Daning and Sadagopan, Aravinth and Düzel, Ümran and Hanquist, Kyle M.},\n\tyear = {2022},\n\tkeywords = {Grassmannian geodesic distance, High-speed fluid–thermal–structural interaction, High-temperature effects, Hypersonic aerothermodynamics, Multi-fidelity surrogate modeling, Multivariate Gaussian process regression, graduate\\_student, own},\n}\n\n\n\n
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\n This study investigates the impact of the high-temperature effect, especially the real gas effect and chemical reactions, on hypersonic aerothermodynamic solutions of double cone and double wedge configurations, as well as the fluid–thermal–structural interaction of a double wedge configuration in hypersonic flow. First, a high-temperature computational fluid dynamics (CFD) code was benchmarked and correlated with experimental results, emphasizing the impact of high-temperature effects as well as turbulence modeling on heat flux prediction. Subsequently, the multi-fidelity multi-variate Gaussian process regression (M2GPR ) method for problems with high-dimensional outputs was developed to create an aerothermal surrogate model. The model achieves a balance between model accuracy and computational cost of sample generation, using the combination of a few high-fidelity samples and many low-fidelity samples. The numerical examples show that, using the M2GPR formulation, the required number of high-fidelity samples may be reduced by over 80% while maintaining an accuracy comparable to the high-fidelity CFD solvers. In addition, a geodesic-distance-based metric is developed to inform the choice of high-dimensional datasets of different fidelities for the M2GPR surrogate with improved accuracy. Finally, the aerothermal surrogate was applied to study the impact of the high-temperature effect on the aerothermoelastic response of a hypersonic skin panel, emphasizing the necessity of the accurate characterization of the localized heat flux for reasonable assessment of the response of a compliant structure in high-speed high-temperature flowfield.\n
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\n \n\n \n \n Durston, D.\n\n\n \n \n \n \n NASA Supersonics Research - Leading Toward Quiet Supersonic Flight!!.\n \n \n \n\n\n \n\n\n\n 2022.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@misc{durston2022,\n\taddress = {Oshkosh, WI},\n\ttitle = {{NASA} {Supersonics} {Research} - {Leading} {Toward} {Quiet} {Supersonic} {Flight}!!},\n\tauthor = {Durston, Don},\n\tyear = {2022},\n}\n\n\n\n
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\n \n\n \n \n Qiu, T.; Zhao, M.; Li, Y.; Li, C.; and Ge, W.\n\n\n \n \n \n \n Multiscale Modeling of Gas–Solid Surface Interactions Under High-Temperature Gas Effect.\n \n \n \n\n\n \n\n\n\n Journal of Thermophysics and Heat Transfer,1–13. June 2022.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@article{qiu2022,\n\ttitle = {Multiscale {Modeling} of {Gas}–{Solid} {Surface} {Interactions} {Under} {High}-{Temperature} {Gas} {Effect}},\n\tdoi = {10.2514/1.T6456},\n\tjournal = {Journal of Thermophysics and Heat Transfer},\n\tauthor = {Qiu, Tianhao and Zhao, Mingcan and Li, Yanping and Li, Chengxiang and Ge, Wei},\n\tmonth = jun,\n\tyear = {2022},\n\tpages = {1--13},\n}\n\n\n\n
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\n \n\n \n \n Gimelshein, S. F.; Wysong, I. J.; Fangman, A. J.; Andrienko, D. A.; Kunova, O. V.; Kustova, E. V.; Morgado, F.; Garbacz, C.; Fossati, M.; and Hanquist, K. M.\n\n\n \n \n \n \n Kinetic and Continuum Modeling of High-Temperature Air Relaxation.\n \n \n \n\n\n \n\n\n\n Journal of Thermophysics and Heat Transfer,1–23. 2022.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{gimelshein2022,\n\ttitle = {Kinetic and {Continuum} {Modeling} of {High}-{Temperature} {Air} {Relaxation}},\n\tdoi = {10.2514/1.T6462},\n\tabstract = {Fully kinetic, vibrationally kinetic, and continuum solvers with varying model fidelity are used in this work to model the high-temperature relaxation of air in 7230 and 15,000 K adiabatic heat bat...},\n\tjournal = {Journal of Thermophysics and Heat Transfer},\n\tauthor = {Gimelshein, Sergey F. and Wysong, Ingrid J. and Fangman, Alexander J. and Andrienko, Daniil A. and Kunova, Olga V. and Kustova, Elena V. and Morgado, Fabio and Garbacz, Catarina and Fossati, Marco and Hanquist, Kyle M.},\n\tyear = {2022},\n\tkeywords = {CFD, Chemical Equilibrium, Direct Simulation Monte Carlo, Heat Flux, High Enthalpy Shock Tunnel, Hypersonic Flows, Nonequilibrium Thermochemistry, Nonequilibrium Vibrational Chemical Kinetics, Stagnation Point, Vibrational Energy, own},\n\tpages = {1--23},\n}\n\n\n\n
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\n Fully kinetic, vibrationally kinetic, and continuum solvers with varying model fidelity are used in this work to model the high-temperature relaxation of air in 7230 and 15,000 K adiabatic heat bat...\n
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\n \n\n \n \n Gimelshein, S. F.; Wysong, I. J.; Fangman, A. J.; Andrienko, D. A.; Kunova, O. V.; Kustova, E. V.; Garbacz, C.; Fossati, M.; and Hanquist, K. M.\n\n\n \n \n \n \n Kinetic and Continuum Modeling of High-Temperature Oxygen and Nitrogen Binary Mixtures.\n \n \n \n\n\n \n\n\n\n Journal of Thermophysics and Heat Transfer,1–20. 2022.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n\n\n\n
\n 
@article{gimelshein2022c,\n\ttitle = {Kinetic and {Continuum} {Modeling} of {High}-{Temperature} {Oxygen} and {Nitrogen} {Binary} {Mixtures}},\n\tdoi = {10.2514/1.T6258},\n\tabstract = {The present paper provides a comprehensive comparative analysis of thermochemistry models of various fidelity levels developed in leading research groups around the world. Fully kinetic, hybrid kin...},\n\tjournal = {Journal of Thermophysics and Heat Transfer},\n\tauthor = {Gimelshein, Sergey F. and Wysong, Ingrid J. and Fangman, Alexander J. and Andrienko, Daniil A. and Kunova, Olga V. and Kustova, Elena V. and Garbacz, Catarina and Fossati, Marco and Hanquist, Kyle M.},\n\tyear = {2022},\n\tkeywords = {own},\n\tpages = {1--20},\n}\n\n\n\n
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\n The present paper provides a comprehensive comparative analysis of thermochemistry models of various fidelity levels developed in leading research groups around the world. Fully kinetic, hybrid kin...\n
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\n \n\n \n \n Tumuklu, O.; and Hanquist, K. M.\n\n\n \n \n \n \n Hypersonic Turbulence Modeling from Rarefied to Continuum Regimes.\n \n \n \n\n\n \n\n\n\n 2022.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n\n\n\n
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@misc{tumuklu2022b,\n\taddress = {32nd International Symposium on Rarefied Gas Dynamics},\n\ttype = {Conference {Presentation}},\n\ttitle = {Hypersonic {Turbulence} {Modeling} from {Rarefied} to {Continuum} {Regimes}},\n\tauthor = {Tumuklu, Ozgur and Hanquist, Kyle M.},\n\tyear = {2022},\n\tkeywords = {own, presentation},\n}\n\n\n\n
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\n \n\n \n \n Morgado, F.; Garbacz, C.; and Fossati, M.\n\n\n \n \n \n \n Impact of Anisotropic Mesh Adaptation on the Aerothermodynamics of Atmospheric Reentry.\n \n \n \n\n\n \n\n\n\n AIAA Journal, 60(7): 3973–3989. July 2022.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{morgado2022,\n\ttitle = {Impact of {Anisotropic} {Mesh} {Adaptation} on the {Aerothermodynamics} of {Atmospheric} {Reentry}},\n\tvolume = {60},\n\tissn = {0001-1452, 1533-385X},\n\tdoi = {10.2514/1.J061071},\n\tlanguage = {en},\n\tnumber = {7},\n\turldate = {2023-01-12},\n\tjournal = {AIAA Journal},\n\tauthor = {Morgado, Fábio and Garbacz, Catarina and Fossati, Marco},\n\tmonth = jul,\n\tyear = {2022},\n\tpages = {3973--3989},\n}\n\n\n\n
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\n \n\n \n \n Vasile, J. D; Fresconi, F.; DeSpirito, J.; Duca, M.; Recchia, T.; Grantham, B.; Bowersox, R. D W; and White, E. B\n\n\n \n \n \n \n High-speed Army Reference Vehicle.\n \n \n \n\n\n \n\n\n\n Technical Report ARL-TN-1128, Army Research Laboratory, 2022.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@techreport{vasile2022,\n\ttitle = {High-speed {Army} {Reference} {Vehicle}},\n\tlanguage = {en},\n\tnumber = {ARL-TN-1128},\n\tinstitution = {Army Research Laboratory},\n\tauthor = {Vasile, Joseph D and Fresconi, Frank and DeSpirito, James and Duca, Marco and Recchia, Thomas and Grantham, Brian and Bowersox, Rodney D W and White, Edward B},\n\tyear = {2022},\n}\n\n\n\n
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\n \n\n \n \n Chazot, O.\n\n\n \n \n \n \n \n Hypersonic Challenges.\n \n \n \n \n\n\n \n\n\n\n . 2022.\n Publisher: AIAA\n\n\n\n
\n\n\n\n \n \n \"HypersonicPaper\n  \n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{chazot2022,\n\ttitle = {Hypersonic {Challenges}},\n\turl = {https://www.aiaa.org/events-learning/event/2022/04/28/default-calendar/aiaa-webinar-hypersonics-challenges},\n\tauthor = {Chazot, O.},\n\tyear = {2022},\n\tnote = {Publisher: AIAA},\n}\n\n\n\n
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\n \n\n \n \n Tumuklu, O.; and Bellan, J.\n\n\n \n \n \n \n \n Development and Validation Studies of a Multi-purpose DSMC Code.\n \n \n \n \n\n\n \n\n\n\n In 2022. American Institute of Aeronautics and Astronautics Inc, AIAA\n \n\n\n\n
\n\n\n\n \n \n \"DevelopmentPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{tumuklu2022c,\n\ttitle = {Development and {Validation} {Studies} of a {Multi}-purpose {DSMC} {Code}},\n\tisbn = {978-1-62410-631-6},\n\turl = {https://arc.aiaa.org/doi/10.2514/6.2022-2017},\n\tdoi = {10.2514/6.2022-2017},\n\tabstract = {A parallel direct simulation Monte Carlo (DSMC) solver has been developed to ultimately couple with an existing granular code1–3 in order to model positioning-rocket plume expansion in the lunar atmosphere and its interaction with the regolith. The challenge is to develop of a multi-species DSMC efficient model and code to fit the target problem. This model and code are here described and results from the model are compared for validation and verification purposes either with existing experimental data or with similar results from similar simulations of wall-bounded canonical flows. In particular, the modeling of Couette flow with different collision schemes provides an opportunity to select a sufficiently numerically efficient collision model to reduce computational costs. Since the objective of the code is to study expansion flows including the plume species of CO2, N2, and H2 O and their interactions with the multi-species composition of the Moon atmosphere (i.e. Ar, He, and Ne), thermal and mass diffusion of mixtures were also studied to show that the code accurately models multispecies situations. To acquire such an ability, the collision and sampling algorithm of the single species code was improved to handle complex multi-species gas interactions. A good agreement with experimental data is achieved, showing that the code accurately predicts the thermal and mass diffusion coefficients of mixtures. Finally, the expanding nature of the plume results in thermochemical nonequilibrium flow, especially in rarefied environments, due to insufficient collision rates. To this end, the rate and the amount of energy transfer among the translational, rotational, and vibrational modes are tested with the previous numerical data and with analytical results.},\n\tpublisher = {American Institute of Aeronautics and Astronautics Inc, AIAA},\n\tauthor = {Tumuklu, Ozgur and Bellan, Josette},\n\tyear = {2022},\n}\n\n\n\n
\n
\n\n\n
\n A parallel direct simulation Monte Carlo (DSMC) solver has been developed to ultimately couple with an existing granular code1–3 in order to model positioning-rocket plume expansion in the lunar atmosphere and its interaction with the regolith. The challenge is to develop of a multi-species DSMC efficient model and code to fit the target problem. This model and code are here described and results from the model are compared for validation and verification purposes either with existing experimental data or with similar results from similar simulations of wall-bounded canonical flows. In particular, the modeling of Couette flow with different collision schemes provides an opportunity to select a sufficiently numerically efficient collision model to reduce computational costs. Since the objective of the code is to study expansion flows including the plume species of CO2, N2, and H2 O and their interactions with the multi-species composition of the Moon atmosphere (i.e. Ar, He, and Ne), thermal and mass diffusion of mixtures were also studied to show that the code accurately models multispecies situations. To acquire such an ability, the collision and sampling algorithm of the single species code was improved to handle complex multi-species gas interactions. A good agreement with experimental data is achieved, showing that the code accurately predicts the thermal and mass diffusion coefficients of mixtures. Finally, the expanding nature of the plume results in thermochemical nonequilibrium flow, especially in rarefied environments, due to insufficient collision rates. To this end, the rate and the amount of energy transfer among the translational, rotational, and vibrational modes are tested with the previous numerical data and with analytical results.\n
\n\n\n
\n\n\n
\n \n\n \n \n Tumuklu, O.; and Bellan, J.\n\n\n \n \n \n \n \n Development and Validation Studies of a Multi-purpose DSMC Code.\n \n \n \n \n\n\n \n\n\n\n In 2022. American Institute of Aeronautics and Astronautics Inc, AIAA\n \n\n\n\n
\n\n\n\n \n \n \"DevelopmentPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{tumuklu2022,\n\ttitle = {Development and {Validation} {Studies} of a {Multi}-purpose {DSMC} {Code}},\n\tisbn = {978-1-62410-631-6},\n\turl = {https://arc.aiaa.org/doi/10.2514/6.2022-2017},\n\tdoi = {10.2514/6.2022-2017},\n\tabstract = {A parallel direct simulation Monte Carlo (DSMC) solver has been developed to ultimately couple with an existing granular code1–3 in order to model positioning-rocket plume expansion in the lunar atmosphere and its interaction with the regolith. The challenge is to develop of a multi-species DSMC efficient model and code to fit the target problem. This model and code are here described and results from the model are compared for validation and verification purposes either with existing experimental data or with similar results from similar simulations of wall-bounded canonical flows. In particular, the modeling of Couette flow with different collision schemes provides an opportunity to select a sufficiently numerically efficient collision model to reduce computational costs. Since the objective of the code is to study expansion flows including the plume species of CO2, N2, and H2 O and their interactions with the multi-species composition of the Moon atmosphere (i.e. Ar, He, and Ne), thermal and mass diffusion of mixtures were also studied to show that the code accurately models multispecies situations. To acquire such an ability, the collision and sampling algorithm of the single species code was improved to handle complex multi-species gas interactions. A good agreement with experimental data is achieved, showing that the code accurately predicts the thermal and mass diffusion coefficients of mixtures. Finally, the expanding nature of the plume results in thermochemical nonequilibrium flow, especially in rarefied environments, due to insufficient collision rates. To this end, the rate and the amount of energy transfer among the translational, rotational, and vibrational modes are tested with the previous numerical data and with analytical results.},\n\tpublisher = {American Institute of Aeronautics and Astronautics Inc, AIAA},\n\tauthor = {Tumuklu, Ozgur and Bellan, Josette},\n\tyear = {2022},\n}\n\n\n\n
\n
\n\n\n
\n A parallel direct simulation Monte Carlo (DSMC) solver has been developed to ultimately couple with an existing granular code1–3 in order to model positioning-rocket plume expansion in the lunar atmosphere and its interaction with the regolith. The challenge is to develop of a multi-species DSMC efficient model and code to fit the target problem. This model and code are here described and results from the model are compared for validation and verification purposes either with existing experimental data or with similar results from similar simulations of wall-bounded canonical flows. In particular, the modeling of Couette flow with different collision schemes provides an opportunity to select a sufficiently numerically efficient collision model to reduce computational costs. Since the objective of the code is to study expansion flows including the plume species of CO2, N2, and H2 O and their interactions with the multi-species composition of the Moon atmosphere (i.e. Ar, He, and Ne), thermal and mass diffusion of mixtures were also studied to show that the code accurately models multispecies situations. To acquire such an ability, the collision and sampling algorithm of the single species code was improved to handle complex multi-species gas interactions. A good agreement with experimental data is achieved, showing that the code accurately predicts the thermal and mass diffusion coefficients of mixtures. Finally, the expanding nature of the plume results in thermochemical nonequilibrium flow, especially in rarefied environments, due to insufficient collision rates. To this end, the rate and the amount of energy transfer among the translational, rotational, and vibrational modes are tested with the previous numerical data and with analytical results.\n
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\n \n\n \n \n Viladegut, A.; and Chazot, O.\n\n\n \n \n \n \n Catalytic characterization in plasma wind tunnels under the influence of gaseous recombination.\n \n \n \n\n\n \n\n\n\n Physics of Fluids, 34(2): 027108–027108. February 2022.\n Publisher: AIP Publishing LLCAIP Publishing\n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{viladegut2022,\n\ttitle = {Catalytic characterization in plasma wind tunnels under the influence of gaseous recombination},\n\tvolume = {34},\n\tdoi = {10.1063/5.0077603},\n\tabstract = {The catalytic properties of materials used in re-usable thermal protection systems (TPSs) of re-entry vehicles are mainly characterized in plasma wind tunnels. These facilities are adequate to repr...},\n\tnumber = {2},\n\tjournal = {Physics of Fluids},\n\tauthor = {Viladegut, A. and Chazot, O.},\n\tmonth = feb,\n\tyear = {2022},\n\tnote = {Publisher: AIP Publishing LLCAIP Publishing},\n\tpages = {027108--027108},\n}\n\n\n\n
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\n The catalytic properties of materials used in re-usable thermal protection systems (TPSs) of re-entry vehicles are mainly characterized in plasma wind tunnels. These facilities are adequate to repr...\n
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\n \n\n \n \n McKown, Q. E.; Kazemba, C. D.; Stern, E. C.; and Brock, J. M.\n\n\n \n \n \n \n \n Attitude Reconstruction of Free-Flight CFD Generated Trajectories Using Non-Linear Pitch Damping Coefficient Curv.\n \n \n \n \n\n\n \n\n\n\n In 2022. AIAA Paper 2022-1169\n \n\n\n\n
\n\n\n\n \n \n \"AttitudePaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{mckown2022,\n\ttitle = {Attitude {Reconstruction} of {Free}-{Flight} {CFD} {Generated} {Trajectories} {Using} {Non}-{Linear} {Pitch} {Damping} {Coefficient} {Curv}},\n\tisbn = {978-1-62410-631-6},\n\turl = {https://arc.aiaa.org/doi/10.2514/6.2022-1169},\n\tdoi = {10.2514/6.2022-1169},\n\tabstract = {Attitude history reconstruction of Free-flight CFD generated trajectories with non-linear pitch damping coefficient curves is investigated. Free-flight CFD simulations of the capsule shape used for the Genesis sample return mission and the upcoming Dragonfly mission to Titan are conducted for 1-, 2-, and 3-degree-of-freedom cases. Two different data reduction methodologies are employed to derive a pitch damping curve as a function of instantaneous angle of attack. These curves are then used to reconstruct the attitude history of the body which is compared to the raw simulation results. While both data reduction methods produce pitch damping curves that can generally reconstruct the motion seen in the Free-flight simulations, it is found that optimization of the pitch damping curve using an inverse estimation process yields superior and more generalizable results. Further refinement of this technique could allow pitch damping curves derived using CFD to serve as a capability complementary to existing techniques for dynamic stability characterization.},\n\tpublisher = {AIAA Paper 2022-1169},\n\tauthor = {McKown, Quincy E. and Kazemba, Cole D. and Stern, Eric C. and Brock, Joseph M.},\n\tyear = {2022},\n}\n\n\n\n
\n
\n\n\n
\n Attitude history reconstruction of Free-flight CFD generated trajectories with non-linear pitch damping coefficient curves is investigated. Free-flight CFD simulations of the capsule shape used for the Genesis sample return mission and the upcoming Dragonfly mission to Titan are conducted for 1-, 2-, and 3-degree-of-freedom cases. Two different data reduction methodologies are employed to derive a pitch damping curve as a function of instantaneous angle of attack. These curves are then used to reconstruct the attitude history of the body which is compared to the raw simulation results. While both data reduction methods produce pitch damping curves that can generally reconstruct the motion seen in the Free-flight simulations, it is found that optimization of the pitch damping curve using an inverse estimation process yields superior and more generalizable results. Further refinement of this technique could allow pitch damping curves derived using CFD to serve as a capability complementary to existing techniques for dynamic stability characterization.\n
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\n \n\n \n \n Lynch, K. P.; Miller, N. E.; Guildenbecher, D. R.; Butler, L.; and Gordeyev, S.\n\n\n \n \n \n \n Aero-Optical Measurements of a Mach 8 Boundary Layer.\n \n \n \n\n\n \n\n\n\n AIAA Journal,1–11. 2022.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{lynch2022,\n\ttitle = {Aero-{Optical} {Measurements} of a {Mach} 8 {Boundary} {Layer}},\n\tissn = {0001-1452},\n\tdoi = {10.2514/1.J062363},\n\tabstract = {Measurements are presented of the aero-optic distortion produced by a Mach 8 turbulent boundary layer in the Sandia Hypersonic Wind Tunnel. Flat optical windows installed in conformal test section walls enabled a double-pass arrangement of a collimated laser beam. The distortion of this beam was imaged by a high-speed Shack–Hartmann sensor using variable aperture sizes at a sampling rate of up to 1.75 MHz. Analysis is performed using two processing methods to extract the aero-optic distortion from the data: 1) a stitching method is applied to extract wavefronts without bias from a limited aperture size, and 2) a novel de-aliasing algorithm is proposed to extract convective-only deflection angle spectra and is demonstrated to correctly quantify the physical spectra even for relatively low sampling rates. Measurements of speed and size of large-scale convecting aero-optical structures are also presented. Overall levels of aero-optic distortions were estimated, and the results are compared with an existing theoretical model. It is shown that this model underpredicts the measured distortions regardless of the processing method used. Possible explanations for this discrepancy are presented. Finally, levels of the global streamwise jitter were estimated for different aperture sizes and compared with the results for the subsonic boundary layer. The results represent to-date the highest Mach number for which aero-optic boundary-layer distortion measurements are available.},\n\turldate = {2023-02-22},\n\tjournal = {AIAA Journal},\n\tauthor = {Lynch, Kyle P. and Miller, Nathan E. and Guildenbecher, Daniel R. and Butler, Luke and Gordeyev, Stanislav},\n\tyear = {2022},\n\tpages = {1--11},\n}\n\n\n\n
\n
\n\n\n
\n Measurements are presented of the aero-optic distortion produced by a Mach 8 turbulent boundary layer in the Sandia Hypersonic Wind Tunnel. Flat optical windows installed in conformal test section walls enabled a double-pass arrangement of a collimated laser beam. The distortion of this beam was imaged by a high-speed Shack–Hartmann sensor using variable aperture sizes at a sampling rate of up to 1.75 MHz. Analysis is performed using two processing methods to extract the aero-optic distortion from the data: 1) a stitching method is applied to extract wavefronts without bias from a limited aperture size, and 2) a novel de-aliasing algorithm is proposed to extract convective-only deflection angle spectra and is demonstrated to correctly quantify the physical spectra even for relatively low sampling rates. Measurements of speed and size of large-scale convecting aero-optical structures are also presented. Overall levels of aero-optic distortions were estimated, and the results are compared with an existing theoretical model. It is shown that this model underpredicts the measured distortions regardless of the processing method used. Possible explanations for this discrepancy are presented. Finally, levels of the global streamwise jitter were estimated for different aperture sizes and compared with the results for the subsonic boundary layer. The results represent to-date the highest Mach number for which aero-optic boundary-layer distortion measurements are available.\n
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\n \n\n \n \n Tumuklu, O.; Bellan, J. R.; and Hanquist, K. M.\n\n\n \n \n \n \n A hybrid DSMC-continuum formulation for jet expansion into rarefied flows.\n \n \n \n\n\n \n\n\n\n 2022.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n\n\n\n
\n 
@misc{tumuklu2022a,\n\taddress = {32nd International Symposium on Rarefied Gas Dynamics},\n\ttitle = {A hybrid {DSMC}-continuum formulation for jet expansion into rarefied flows},\n\tauthor = {Tumuklu, Ozgur and Bellan, Josette R. and Hanquist, Kyle M.},\n\tyear = {2022},\n\tkeywords = {own, presentation},\n}\n\n\n\n
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\n  \n 2021\n \n \n (48)\n \n \n
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\n \n\n \n \n Yu, S.; Ni, X.; and Chen, F.\n\n\n \n \n \n \n \n CFD Simulation Strategy for Hypersonic Aerodynamic Heating around a Blunt Biconic.\n \n \n \n \n\n\n \n\n\n\n International Journal of Aerospace Engineering, 2021: 1–11. April 2021.\n \n\n\n\n
\n\n\n\n \n \n \"CFDPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{yu_cfd_2021,\n\ttitle = {{CFD} {Simulation} {Strategy} for {Hypersonic} {Aerodynamic} {Heating} around a {Blunt} {Biconic}},\n\tvolume = {2021},\n\tcopyright = {https://creativecommons.org/licenses/by/4.0/},\n\tissn = {1687-5974, 1687-5966},\n\turl = {https://www.hindawi.com/journals/ijae/2021/8885074/},\n\tdoi = {10.1155/2021/8885074},\n\tabstract = {The design of the thermal protection system requires high-precision and high-reliability CFD simulation for validation. To accurately predict the hypersonic aerodynamic heating, an overall simulation strategy based on mutual selection is proposed. Foremost, the grid criterion based on the wall cell Reynolds number is developed. Subsequently, the dependence of the turbulence model and the discretization scheme is considered. It is suggested that the appropriate value of wall cell Reynolds number is 1 through careful comparison between one another and with the available experimental data. The excessive number of cells is not recommended due to time-consuming computation. It can be seen from the results that the combination of the AUSM+ discretization scheme and the Spalart-Allmaras turbulence model has the highest accuracy. In this work, the heat flux error of the stagnation point is within 1\\%, and the overall average relative error is within 10\\%.},\n\turldate = {2025-03-04},\n\tjournal = {International Journal of Aerospace Engineering},\n\tauthor = {Yu, Shutian and Ni, Xinyue and Chen, Fansheng},\n\teditor = {Xie, Kan},\n\tmonth = apr,\n\tyear = {2021},\n\tpages = {1--11},\n}\n\n\n\n
\n
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\n The design of the thermal protection system requires high-precision and high-reliability CFD simulation for validation. To accurately predict the hypersonic aerodynamic heating, an overall simulation strategy based on mutual selection is proposed. Foremost, the grid criterion based on the wall cell Reynolds number is developed. Subsequently, the dependence of the turbulence model and the discretization scheme is considered. It is suggested that the appropriate value of wall cell Reynolds number is 1 through careful comparison between one another and with the available experimental data. The excessive number of cells is not recommended due to time-consuming computation. It can be seen from the results that the combination of the AUSM+ discretization scheme and the Spalart-Allmaras turbulence model has the highest accuracy. In this work, the heat flux error of the stagnation point is within 1%, and the overall average relative error is within 10%.\n
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\n \n\n \n \n Slater, J.\n\n\n \n \n \n \n \n Uncertainty and Error in CFD Simulations.\n \n \n \n \n\n\n \n\n\n\n February 2021.\n \n\n\n\n
\n\n\n\n \n \n \"UncertaintyPaper\n  \n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@misc{slater2021,\n\ttitle = {Uncertainty and {Error} in {CFD} {Simulations}},\n\turl = {https://www.grc.nasa.gov/WWW/wind/valid/tutorial/errors.html},\n\tjournal = {NPARC Alliance CFD Verification and Validation Web Site},\n\tauthor = {Slater, John},\n\tmonth = feb,\n\tyear = {2021},\n}\n\n\n\n
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\n \n\n \n \n Li, W.; Zhao, D.; Chen, X.; Zhu, L.; and Ni, S.\n\n\n \n \n \n \n Numerical Investigation of Inlet Thermodynamic Conditions on Solid Fuel Ramjet Performances.\n \n \n \n\n\n \n\n\n\n International Journal of Aerospace Engineering, 2021. January 2021.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{li2021,\n\ttitle = {Numerical {Investigation} of {Inlet} {Thermodynamic} {Conditions} on {Solid} {Fuel} {Ramjet} {Performances}},\n\tvolume = {2021},\n\tdoi = {10.1155/2021/8868288},\n\tabstract = {In this work, 2D numerical RANS (Reynolds Average Navier-Stokes) simulations were carried out to investigate the thermodynamic performance of a solid fuel ramjet (SFRJ) with different inlet conditions. This is achieved by using an in-house FORTRAN code to simulate a 2D turbulent, reacting, unsteady flow in the ramjet engine. The inlet conditions are characterized by three key parameters: (1) swirl number (), (2) mass flow rate (), and (3) inlet temperature (). With the code numerically validated by benchmarking with a number of computed cases, it is applied to perform systematic studies on the turbulent flow recirculation, combustion, and heat transfer characteristics. It is found that increasing , , or can dramatically enhance the combustion heat release rate, regression rate, and combustor average temperature. Furthermore, the analysis on the chemical reaction intermediate (CO) reveals that the chemical reaction is more sufficient with increased , but . In addition, a secondary vortex is generated at the corner of the backward facing step in the presence of a swirl flow resulting from the instability of the shear layer. Finally, the nonlinear correlations between the heat transfer, combustion characteristics, and flow field characteristics and the corresponding inlet thermodynamic parameters are identified.},\n\tlanguage = {en},\n\turldate = {2024-05-29},\n\tjournal = {International Journal of Aerospace Engineering},\n\tauthor = {Li, Weixuan and Zhao, Dan and Chen, Xiong and Zhu, Liang and Ni, Siliang},\n\tmonth = jan,\n\tyear = {2021},\n}\n\n\n\n\n\n\n\n
\n
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\n In this work, 2D numerical RANS (Reynolds Average Navier-Stokes) simulations were carried out to investigate the thermodynamic performance of a solid fuel ramjet (SFRJ) with different inlet conditions. This is achieved by using an in-house FORTRAN code to simulate a 2D turbulent, reacting, unsteady flow in the ramjet engine. The inlet conditions are characterized by three key parameters: (1) swirl number (), (2) mass flow rate (), and (3) inlet temperature (). With the code numerically validated by benchmarking with a number of computed cases, it is applied to perform systematic studies on the turbulent flow recirculation, combustion, and heat transfer characteristics. It is found that increasing , , or can dramatically enhance the combustion heat release rate, regression rate, and combustor average temperature. Furthermore, the analysis on the chemical reaction intermediate (CO) reveals that the chemical reaction is more sufficient with increased , but . In addition, a secondary vortex is generated at the corner of the backward facing step in the presence of a swirl flow resulting from the instability of the shear layer. Finally, the nonlinear correlations between the heat transfer, combustion characteristics, and flow field characteristics and the corresponding inlet thermodynamic parameters are identified.\n
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\n \n\n \n \n Slater, J.\n\n\n \n \n \n \n \n Uncertainty and Error in CFD Simulations.\n \n \n \n \n\n\n \n\n\n\n February 2021.\n \n\n\n\n
\n\n\n\n \n \n \"UncertaintyPaper\n  \n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@misc{slater2021,\n\ttitle = {Uncertainty and {Error} in {CFD} {Simulations}},\n\turl = {https://www.grc.nasa.gov/WWW/wind/valid/tutorial/errors.html},\n\tjournal = {NPARC Alliance CFD Verification and Validation Web Site},\n\tauthor = {Slater, John},\n\tmonth = feb,\n\tyear = {2021},\n}\n\n\n\n
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\n \n\n \n \n Andrienko, D.; Sahu, R.; Tropina, A.; Miles, R. B.; and Hara, K.\n\n\n \n \n \n \n Computational fluid dynamic model of electron transpiration cooling in weakly ionized air flows.\n \n \n \n\n\n \n\n\n\n In AIAA Scitech 2021 Forum, 2021. AIAA Paper 2021-0684\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{andrienko2021,\n\ttitle = {Computational fluid dynamic model of electron transpiration cooling in weakly ionized air flows},\n\tabstract = {View Video Presentation: https://doi.org/10.2514/6.2021-0684.vidThe present paper is concerned with the computational fluid dynamic model of a cesium-wetted tungsten surface and associated thermionic emission under hypersonic flight conditions. A set of Navier-Stokes equations coupled with the finite-rate cesium-air plasma model and Ohm's law is used to model a two-dimensional viscous, thermally conductive, and thermochemically reactive hypersonic flow. Electron emission is modeled via the Richardson-Dushman equation for saturation current. Additionally, a one-dimensional full fluid moment model of plasma sheath is used to identify the onset of space charge limited emission in the presence of NO+ and Cs+ ions. The computer model, while being actively developed, is aimed to describe a closed-loop operation of an electron transpiration cooling concept of a metallic surface of a leading edge in two-dimensional geometry. A notional geometry of a 1 cm radius of curvature leading edge at Mach 14 and 60 km of altitude with assumed ideal thermionic electron emission for wall temperature of 1500K indicates that significant electron and cesium evaporation cooling is expected, and the emission may not reach the space-charge limit with sufficient amount of ions in the flow.},\n\turldate = {2024-04-30},\n\tbooktitle = {{AIAA} {Scitech} 2021 {Forum}},\n\tpublisher = {AIAA Paper 2021-0684},\n\tauthor = {Andrienko, Daniil and Sahu, Rupali and Tropina, Albina and Miles, Richard B. and Hara, Kentaro},\n\tyear = {2021},\n}\n\n\n\n\n\n\n\n\n\n\n\n
\n
\n\n\n
\n View Video Presentation: https://doi.org/10.2514/6.2021-0684.vidThe present paper is concerned with the computational fluid dynamic model of a cesium-wetted tungsten surface and associated thermionic emission under hypersonic flight conditions. A set of Navier-Stokes equations coupled with the finite-rate cesium-air plasma model and Ohm's law is used to model a two-dimensional viscous, thermally conductive, and thermochemically reactive hypersonic flow. Electron emission is modeled via the Richardson-Dushman equation for saturation current. Additionally, a one-dimensional full fluid moment model of plasma sheath is used to identify the onset of space charge limited emission in the presence of NO+ and Cs+ ions. The computer model, while being actively developed, is aimed to describe a closed-loop operation of an electron transpiration cooling concept of a metallic surface of a leading edge in two-dimensional geometry. A notional geometry of a 1 cm radius of curvature leading edge at Mach 14 and 60 km of altitude with assumed ideal thermionic electron emission for wall temperature of 1500K indicates that significant electron and cesium evaporation cooling is expected, and the emission may not reach the space-charge limit with sufficient amount of ions in the flow.\n
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\n \n\n \n \n Lu, L.; Meng, X.; Mao, Z.; and Karniadakis, G. E.\n\n\n \n \n \n \n DeepXDE: A Deep Learning Library for Solving Differential Equations.\n \n \n \n\n\n \n\n\n\n SIAM Review, 63(1): 208–228. January 2021.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{lu2021,\n\ttitle = {{DeepXDE}: {A} {Deep} {Learning} {Library} for {Solving} {Differential} {Equations}},\n\tvolume = {63},\n\tissn = {0036-1445},\n\tshorttitle = {{DeepXDE}},\n\tdoi = {10.1137/19M1274067},\n\tabstract = {Uncertainty quantification (UQ) in machine learning is currently drawing increasing research interest, driven by the rapid deployment of deep neural networks across different fields, such as computer vision and natural language processing, and by the need for reliable tools in risk-sensitive applications. Recently, various machine learning models have also been developed to tackle problems in the field of scientific computing with applications to computational science and engineering (CSE). Physics-informed neural networks and deep operator networks are two such models for solving partial differential equations (PDEs) and learning operator mappings, respectively. In this regard, a comprehensive study of UQ methods tailored specifically for scientific machine learning (SciML) models has been provided in [A. F. Psaros et al., J. Comput. Phys., 477 (2023), art. 111902]. Nevertheless, and despite their theoretical merit, implementations of these methods are not straightforward, especially in large-scale CSE applications, hindering their broad adoption in both research and industry settings. In this paper, we present an open-source Python library (ŭlhttps://github.com/Crunch-UQ4MI), termed NeuralUQ and accompanied by an educational tutorial, for employing UQ methods for SciML in a convenient and structured manner. The library, designed for both educational and research purposes, supports multiple modern UQ methods and SciML models. It is based on a succinct workflow and facilitates flexible employment and easy extensions by the users. We first present a tutorial of NeuralUQ and subsequently demonstrate its applicability and efficiency in four diverse examples, involving dynamical systems and high-dimensional parametric and time-dependent PDEs.},\n\tnumber = {1},\n\turldate = {2024-04-24},\n\tjournal = {SIAM Review},\n\tauthor = {Lu, Lu and Meng, Xuhui and Mao, Zhiping and Karniadakis, George Em},\n\tmonth = jan,\n\tyear = {2021},\n\tpages = {208--228},\n}\n\n\n\n\n\n\n\n
\n
\n\n\n
\n Uncertainty quantification (UQ) in machine learning is currently drawing increasing research interest, driven by the rapid deployment of deep neural networks across different fields, such as computer vision and natural language processing, and by the need for reliable tools in risk-sensitive applications. Recently, various machine learning models have also been developed to tackle problems in the field of scientific computing with applications to computational science and engineering (CSE). Physics-informed neural networks and deep operator networks are two such models for solving partial differential equations (PDEs) and learning operator mappings, respectively. In this regard, a comprehensive study of UQ methods tailored specifically for scientific machine learning (SciML) models has been provided in [A. F. Psaros et al., J. Comput. Phys., 477 (2023), art. 111902]. Nevertheless, and despite their theoretical merit, implementations of these methods are not straightforward, especially in large-scale CSE applications, hindering their broad adoption in both research and industry settings. In this paper, we present an open-source Python library (ŭlhttps://github.com/Crunch-UQ4MI), termed NeuralUQ and accompanied by an educational tutorial, for employing UQ methods for SciML in a convenient and structured manner. The library, designed for both educational and research purposes, supports multiple modern UQ methods and SciML models. It is based on a succinct workflow and facilitates flexible employment and easy extensions by the users. We first present a tutorial of NeuralUQ and subsequently demonstrate its applicability and efficiency in four diverse examples, involving dynamical systems and high-dimensional parametric and time-dependent PDEs.\n
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\n \n\n \n \n Schiassi, E.; Furfaro, R.; Leake, C.; De Florio, M.; Johnston, H.; and Mortari, D.\n\n\n \n \n \n \n Extreme theory of functional connections: A fast physics-informed neural network method for solving ordinary and partial differential equations.\n \n \n \n\n\n \n\n\n\n Neurocomputing, 457: 334–356. October 2021.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{schiassi2021,\n\ttitle = {Extreme theory of functional connections: {A} fast physics-informed neural network method for solving ordinary and partial differential equations},\n\tvolume = {457},\n\tissn = {0925-2312},\n\tshorttitle = {Extreme theory of functional connections},\n\tdoi = {10.1016/j.neucom.2021.06.015},\n\tabstract = {We present a novel, accurate, fast, and robust physics-informed neural network method for solving problems involving differential equations (DEs), called Extreme Theory of Functional Connections, or X-TFC. The proposed method is a synergy of two recently developed frameworks for solving problems involving DEs: the Theory of Functional Connections TFC, and the Physics-Informed Neural Networks PINN. Here, the latent solution of the DEs is approximated by a TFC constrained expression that employs a Neural Network (NN) as the free-function. The TFC approximated solution form always analytically satisfies the constraints of the DE, while maintaining a NN with unconstrained parameters. X-TFC uses a single-layer NN trained via the Extreme Learning Machine (ELM) algorithm. This choice is based on the approximating properties of the ELM algorithm that reduces the training of the network to a simple least-squares, because the only trainable parameters are the output weights. The proposed methodology was tested over a wide range of problems including the approximation of solutions to linear and nonlinear ordinary DEs (ODEs), systems of ODEs, and partial DEs (PDEs). The results show that, for most of the problems considered, X-TFC achieves high accuracy with low computational time, even for large scale PDEs, without suffering the curse of dimensionality.},\n\turldate = {2024-04-24},\n\tjournal = {Neurocomputing},\n\tauthor = {Schiassi, Enrico and Furfaro, Roberto and Leake, Carl and De Florio, Mario and Johnston, Hunter and Mortari, Daniele},\n\tmonth = oct,\n\tyear = {2021},\n\tkeywords = {Extreme learning machine, Functional interpolation, Least-squares, Numerical methods, Physics-informed neural networks, Universal approximator},\n\tpages = {334--356},\n}\n\n\n\n
\n
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\n We present a novel, accurate, fast, and robust physics-informed neural network method for solving problems involving differential equations (DEs), called Extreme Theory of Functional Connections, or X-TFC. The proposed method is a synergy of two recently developed frameworks for solving problems involving DEs: the Theory of Functional Connections TFC, and the Physics-Informed Neural Networks PINN. Here, the latent solution of the DEs is approximated by a TFC constrained expression that employs a Neural Network (NN) as the free-function. The TFC approximated solution form always analytically satisfies the constraints of the DE, while maintaining a NN with unconstrained parameters. X-TFC uses a single-layer NN trained via the Extreme Learning Machine (ELM) algorithm. This choice is based on the approximating properties of the ELM algorithm that reduces the training of the network to a simple least-squares, because the only trainable parameters are the output weights. The proposed methodology was tested over a wide range of problems including the approximation of solutions to linear and nonlinear ordinary DEs (ODEs), systems of ODEs, and partial DEs (PDEs). The results show that, for most of the problems considered, X-TFC achieves high accuracy with low computational time, even for large scale PDEs, without suffering the curse of dimensionality.\n
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\n \n\n \n \n Liza, M. E.; Burton, G.; and Hanquist, K. M.\n\n\n \n \n \n \n Examining turbulent length scales and flow correlations in a direct numerical simulation study of a hypersonic boundary layer flow produced by a uniform aspect ratio mesh using a high-resolution low dissipation massively parallel CFD code.\n \n \n \n\n\n \n\n\n\n 2021.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n  \n \n 1 download\n \n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n\n\n\n
\n 
@misc{liza2021,\n\taddress = {74th Annual Meeting of the Division of Fluid Dynamics, American Physical Society},\n\ttype = {Conference {Presentation}},\n\ttitle = {Examining turbulent length scales and flow correlations in a direct numerical simulation study of a hypersonic boundary layer flow produced by a uniform aspect ratio mesh using a high-resolution low dissipation massively parallel {CFD} code.},\n\tauthor = {Liza, Martin E. and Burton, Gregory and Hanquist, Kyle M.},\n\tyear = {2021},\n\tkeywords = {own, presentation},\n}\n\n\n\n
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\n \n\n \n \n Aguirre, T. G.; Cramer, C. L.; Cakmak, E.; Lance, M. J.; and Lowden, R. A.\n\n\n \n \n \n \n Processing and microstructure of ZrB2–SiC composite prepared by reactive spark plasma sintering.\n \n \n \n\n\n \n\n\n\n Results in Materials, 11: 100217. September 2021.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{aguirre2021,\n\ttitle = {Processing and microstructure of {ZrB2}–{SiC} composite prepared by reactive spark plasma sintering},\n\tvolume = {11},\n\tissn = {2590-048X},\n\tdoi = {10.1016/j.rinma.2021.100217},\n\tabstract = {In-situ formation of ZrB2–SiC composites was investigated by reactive spark plasma sintering of precursor powders according to the reaction B4C + 2ZrC + 3Si → 3SiC + 2ZrB2. The reaction and process presented here involves a diffusion reaction between B4C and ZrC which facilitates the formation of ZrB2, while liquid phase sintering of silicon facilitates atomic diffusion and combines with free C from the B4C and ZrC reaction to form SiC within minutes of heating and there were some residual unreacted precursor materials. An interpenetrating matrix of ZrB2–SiC was formed that shows increased fracture toughness (6.03 ± 0.45 MPa m1/2) despite relatively low density (95 \\%).},\n\turldate = {2024-04-24},\n\tjournal = {Results in Materials},\n\tauthor = {Aguirre, Trevor G. and Cramer, Corson L. and Cakmak, Ercan and Lance, Michael J. and Lowden, Richard A.},\n\tmonth = sep,\n\tyear = {2021},\n\tpages = {100217},\n}\n\n\n\n\n\n\n\n\n\n\n\n
\n
\n\n\n
\n In-situ formation of ZrB2–SiC composites was investigated by reactive spark plasma sintering of precursor powders according to the reaction B4C + 2ZrC + 3Si → 3SiC + 2ZrB2. The reaction and process presented here involves a diffusion reaction between B4C and ZrC which facilitates the formation of ZrB2, while liquid phase sintering of silicon facilitates atomic diffusion and combines with free C from the B4C and ZrC reaction to form SiC within minutes of heating and there were some residual unreacted precursor materials. An interpenetrating matrix of ZrB2–SiC was formed that shows increased fracture toughness (6.03 ± 0.45 MPa m1/2) despite relatively low density (95 %).\n
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\n \n\n \n \n Johnson, G. R.; and Campanell, M. D.\n\n\n \n \n \n \n Effects of emitting surfaces and trapped ions on the sheath physics and current flow in multidimensional plasma systems.\n \n \n \n\n\n \n\n\n\n Plasma Sources Science and Technology, 30(1): 015003. January 2021.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{johnson2021,\n\ttitle = {Effects of emitting surfaces and trapped ions on the sheath physics and current flow in multidimensional plasma systems},\n\tvolume = {30},\n\tissn = {0963-0252},\n\tdoi = {10.1088/1361-6595/abcc7b},\n\tabstract = {Recent one-dimensional simulations of planar sheaths with strong electron emission have shown that trapping of charge-exchange ions causes transitions from space-charge limited (SCL) to inverse sheaths. However, multidimensional emitting sheath phenomena with collisions remained unexplored, due in part to high computational cost. We developed a novel continuum kinetic code to study the sheath physics, current flow and potential distributions in two-dimensional unmagnetized configurations with emitting surfaces. For small negatively biased thermionic cathodes in a plasma, the cathode sheath can exist in an equilibrium SCL state. The SCL sheath carries an immense density of trapped ions, neutralized by thermoelectrons, within the potential well of the virtual cathode. For further increases of emitted flux, the trapped ion cloud expands in space. The trapped ion space charge causes an increase of thermionic current far beyond the saturation limit predicted by conventional collisionless SCL sheath models without ion trapping. For sufficiently strong emission, the trapped ion cloud consumes the entire 2D plasma domain, forming a mode with globally confined ions and an inverse sheath at the cathode. In situations where the emitted flux is fixed and the bias is swept (e.g. emissive probe), the trapped ions cause a large thermionic current to escape for all biases below the plasma potential. Strong suppression of the thermionic emission, required for the probe to float, only occurs when the probe is above the plasma potential.},\n\tlanguage = {en},\n\tnumber = {1},\n\turldate = {2024-04-23},\n\tjournal = {Plasma Sources Science and Technology},\n\tauthor = {Johnson, G. R. and Campanell, M. D.},\n\tmonth = jan,\n\tyear = {2021},\n\tpages = {015003},\n}\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n
\n
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\n Recent one-dimensional simulations of planar sheaths with strong electron emission have shown that trapping of charge-exchange ions causes transitions from space-charge limited (SCL) to inverse sheaths. However, multidimensional emitting sheath phenomena with collisions remained unexplored, due in part to high computational cost. We developed a novel continuum kinetic code to study the sheath physics, current flow and potential distributions in two-dimensional unmagnetized configurations with emitting surfaces. For small negatively biased thermionic cathodes in a plasma, the cathode sheath can exist in an equilibrium SCL state. The SCL sheath carries an immense density of trapped ions, neutralized by thermoelectrons, within the potential well of the virtual cathode. For further increases of emitted flux, the trapped ion cloud expands in space. The trapped ion space charge causes an increase of thermionic current far beyond the saturation limit predicted by conventional collisionless SCL sheath models without ion trapping. For sufficiently strong emission, the trapped ion cloud consumes the entire 2D plasma domain, forming a mode with globally confined ions and an inverse sheath at the cathode. In situations where the emitted flux is fixed and the bias is swept (e.g. emissive probe), the trapped ions cause a large thermionic current to escape for all biases below the plasma potential. Strong suppression of the thermionic emission, required for the probe to float, only occurs when the probe is above the plasma potential.\n
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\n \n\n \n \n De Florio, M.; Schiassi, E.; Ganapol, B. D.; and Furfaro, R.\n\n\n \n \n \n \n Physics-informed neural networks for rarefied-gas dynamics: Thermal creep flow in the Bhatnagar–Gross–Krook approximation.\n \n \n \n\n\n \n\n\n\n Physics of Fluids, 33(4): 047110. April 2021.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{deflorio2021,\n\ttitle = {Physics-informed neural networks for rarefied-gas dynamics: {Thermal} creep flow in the {Bhatnagar}–{Gross}–{Krook} approximation},\n\tvolume = {33},\n\tshorttitle = {Physics-informed neural networks for rarefied-gas dynamics},\n\tdoi = {10.1063/5.0046181},\n\tabstract = {This work aims at accurately solve a thermal creep flow in a plane channel problem, as a class of rarefied-gas dynamics problems, using Physics-Informed Neural Networks (PINNs). We develop a particular PINN framework where the solution of the problem is represented by the Constrained Expressions (CE) prescribed by the recently introduced Theory of Functional Connections (TFC). CEs are represented by a sum of a free-function and a functional (e.g., function of functions) that analytically satisfies the problem constraints regardless to the choice of the free-function. The latter is represented by a shallow Neural Network (NN). Here, the resulting PINN-TFC approach is employed to solve the Boltzmann equation in the Bhatnagar–Gross–Krook approximation modeling the Thermal Creep Flow in a plane channel. We test three different types of shallow NNs, i.e., standard shallow NN, Chebyshev NN (ChNN), and Legendre NN (LeNN). For all the three cases the unknown solutions are computed via the extreme learning machine algorithm. We show that with all these networks we can achieve accurate solutions with a fast training time. In particular, with ChNN and LeNN we are able to match all the available benchmarks.},\n\tlanguage = {en},\n\tnumber = {4},\n\turldate = {2024-01-24},\n\tjournal = {Physics of Fluids},\n\tauthor = {De Florio, Mario and Schiassi, Enrico and Ganapol, Barry D. and Furfaro, Roberto},\n\tmonth = apr,\n\tyear = {2021},\n\tpages = {047110},\n}\n\n\n\n\n\n\n\n
\n
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\n This work aims at accurately solve a thermal creep flow in a plane channel problem, as a class of rarefied-gas dynamics problems, using Physics-Informed Neural Networks (PINNs). We develop a particular PINN framework where the solution of the problem is represented by the Constrained Expressions (CE) prescribed by the recently introduced Theory of Functional Connections (TFC). CEs are represented by a sum of a free-function and a functional (e.g., function of functions) that analytically satisfies the problem constraints regardless to the choice of the free-function. The latter is represented by a shallow Neural Network (NN). Here, the resulting PINN-TFC approach is employed to solve the Boltzmann equation in the Bhatnagar–Gross–Krook approximation modeling the Thermal Creep Flow in a plane channel. We test three different types of shallow NNs, i.e., standard shallow NN, Chebyshev NN (ChNN), and Legendre NN (LeNN). For all the three cases the unknown solutions are computed via the extreme learning machine algorithm. We show that with all these networks we can achieve accurate solutions with a fast training time. In particular, with ChNN and LeNN we are able to match all the available benchmarks.\n
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\n \n\n \n \n Garbacz, C.; Morgado, F.; Fossati, M.; Maier, W. T; Needels, J.; Alonso, J. J.; Capitelli, M.; Scoggins, J. B.; Magin, T. E.; Liza, M.; and Hanquist, K. M.\n\n\n \n \n \n \n SU2-NEMO: An Open-Source Framework for Nonequilibrium Flows.\n \n \n \n\n\n \n\n\n\n In 2021. \n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{garbacz2021a,\n\ttitle = {{SU2}-{NEMO}: {An} {Open}-{Source} {Framework} for {Nonequilibrium} {Flows}},\n\tauthor = {Garbacz, Catrina and Morgado, Fabio and Fossati, Marco and Maier, Walter T and Needels, Jacob and Alonso, Juan J. and Capitelli, M. and Scoggins, James B. and Magin, Thierry E. and Liza, Martin and Hanquist, Kyle M.},\n\tyear = {2021},\n}\n\n\n\n
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\n \n\n \n \n Campbell, N. S.; Hanquist, K.; Morin, A.; Meyers, J.; and Boyd, I.\n\n\n \n \n \n \n Evaluation of Computational Models for Electron Transpiration Cooling.\n \n \n \n\n\n \n\n\n\n Aerospace, 8(9). September 2021.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{campbell_evaluation_2021,\n\ttitle = {Evaluation of {Computational} {Models} for {Electron} {Transpiration} {Cooling}},\n\tvolume = {8},\n\tdoi = {10.3390/AEROSPACE8090243},\n\tabstract = {Recent developments in the world of hypersonic flight have brought increased attention to the thermal response of materials exposed to high-enthalpy gases. One promising concept is electron transpiration cooling (ETC) that provides the prospect of a passive heat removal mechanism, rivaling and possibly outperforming that of radiative cooling. In this work, non-equilibrium CFD simulations are performed to evaluate the possible roles of this cooling mode under high-enthalpy conditions obtainable in plasma torch ground-test facilities capable of long flow times. The work focuses on the test case of argon gas being heated to achieve enthalpies equivalent to post-shock conditions experienced by a vehicle flying through the atmosphere at hypersonic speed. Simulations are performed at a range of conditions and are used to calibrate direct comparisons between torch operating conditions and resulting flow properties. These comparisons highlight important modeling considerations for simulating long-duration, hot chamber tests. Simulation results correspond well with the experimental measurements of gas temperature, material surface temperature as well as measured current generated in the test article. Theoretical methods taking into consideration space charge limitations are presented and applied to provide design suggestions to boost the ETC effect in future experiments.},\n\tnumber = {9},\n\tjournal = {Aerospace},\n\tauthor = {Campbell, Nicholas S. and Hanquist, Kyle and Morin, Andrew and Meyers, Jason and Boyd, Iain},\n\tmonth = sep,\n\tyear = {2021},\n\tkeywords = {equilibrium gas dynamics, gas, hypersonic flight, non, plasma and ionized flows, surface interaction},\n}\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n
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\n Recent developments in the world of hypersonic flight have brought increased attention to the thermal response of materials exposed to high-enthalpy gases. One promising concept is electron transpiration cooling (ETC) that provides the prospect of a passive heat removal mechanism, rivaling and possibly outperforming that of radiative cooling. In this work, non-equilibrium CFD simulations are performed to evaluate the possible roles of this cooling mode under high-enthalpy conditions obtainable in plasma torch ground-test facilities capable of long flow times. The work focuses on the test case of argon gas being heated to achieve enthalpies equivalent to post-shock conditions experienced by a vehicle flying through the atmosphere at hypersonic speed. Simulations are performed at a range of conditions and are used to calibrate direct comparisons between torch operating conditions and resulting flow properties. These comparisons highlight important modeling considerations for simulating long-duration, hot chamber tests. Simulation results correspond well with the experimental measurements of gas temperature, material surface temperature as well as measured current generated in the test article. Theoretical methods taking into consideration space charge limitations are presented and applied to provide design suggestions to boost the ETC effect in future experiments.\n
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\n \n\n \n \n Petrie, C. M.; Schrell, A. M.; Leonard, D. N.; Yang, Y.; Jolly, B. C.; and Terrani, K. A.\n\n\n \n \n \n \n \n Embedded sensors in additively manufactured silicon carbide.\n \n \n \n \n\n\n \n\n\n\n Journal of Nuclear Materials, 552: 153012. August 2021.\n \n\n\n\n
\n\n\n\n \n \n \"EmbeddedPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{petrie_embedded_2021,\n\ttitle = {Embedded sensors in additively manufactured silicon carbide},\n\tvolume = {552},\n\tissn = {0022-3115},\n\turl = {https://www.sciencedirect.com/science/article/pii/S002231152100235X},\n\tdoi = {10.1016/j.jnucmat.2021.153012},\n\tabstract = {Silicon carbide (SiC) components are being considered for a wide range of nuclear applications due to their high-temperature strength retention, low neutron absorption, chemical inertness, and dimensional stability under neutron irradiation. However, machining and joining of SiC components have traditionally limited its application to relatively simple geometries. Recent work has demonstrated additive manufacturing of complex, high-purity, crystalline SiC components using a combination of binder jet printing and densification via chemical vapor infiltration (CVI). The process lends itself to embedding of fuel, absorbers, moderators, and sensors at strategic locations within a component. The latter could allow for enhanced in situ performance monitoring of limiting fuel temperatures, self-shielded neutron flux, and potentially spatially distributed strain within complex SiC components if sensors can be successfully embedded during CVI. This work describes (1) methods for embedding sensors; (2) thermodynamic analyses and material compatibility testing for identifying sensors capable of surviving high temperatures and exposure to hydrogen and hydrogen chloride during CVI; and (3) nuclear applications for embedded sensors, including potential failure modes during fabrication and during reactor operation. Molybdenum-sheathed thermocouples were successfully embedded in a complex SiC component, whereas niobium-sheathed high-temperature irradiation-resistant thermocouples started to drift as soon as the reactant gases were introduced and ultimately failed during CVI due to severe constrained expansion, potentially resulting from niobium hydride formation in the low-temperature region of the CVI system. Optical fibers were successfully embedded in SiC, but further work is needed to protect the fragile fiber leads after their protective coatings are removed during CVI.},\n\turldate = {2023-10-30},\n\tjournal = {Journal of Nuclear Materials},\n\tauthor = {Petrie, Christian M. and Schrell, Adrian M. and Leonard, Donovan N. and Yang, Ying and Jolly, Brian C. and Terrani, Kurt A.},\n\tmonth = aug,\n\tyear = {2021},\n\tkeywords = {Additive manufacturing, Embedded, Fiber-optics, Sensors, Silicon carbide, Thermocouples},\n\tpages = {153012},\n}\n\n\n\n\n\n\n\n
\n
\n\n\n
\n Silicon carbide (SiC) components are being considered for a wide range of nuclear applications due to their high-temperature strength retention, low neutron absorption, chemical inertness, and dimensional stability under neutron irradiation. However, machining and joining of SiC components have traditionally limited its application to relatively simple geometries. Recent work has demonstrated additive manufacturing of complex, high-purity, crystalline SiC components using a combination of binder jet printing and densification via chemical vapor infiltration (CVI). The process lends itself to embedding of fuel, absorbers, moderators, and sensors at strategic locations within a component. The latter could allow for enhanced in situ performance monitoring of limiting fuel temperatures, self-shielded neutron flux, and potentially spatially distributed strain within complex SiC components if sensors can be successfully embedded during CVI. This work describes (1) methods for embedding sensors; (2) thermodynamic analyses and material compatibility testing for identifying sensors capable of surviving high temperatures and exposure to hydrogen and hydrogen chloride during CVI; and (3) nuclear applications for embedded sensors, including potential failure modes during fabrication and during reactor operation. Molybdenum-sheathed thermocouples were successfully embedded in a complex SiC component, whereas niobium-sheathed high-temperature irradiation-resistant thermocouples started to drift as soon as the reactant gases were introduced and ultimately failed during CVI due to severe constrained expansion, potentially resulting from niobium hydride formation in the low-temperature region of the CVI system. Optical fibers were successfully embedded in SiC, but further work is needed to protect the fragile fiber leads after their protective coatings are removed during CVI.\n
\n\n\n
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\n \n\n \n \n Montón, A.; Abdelmoula, M.; Küçüktürk, G.; Maury, F.; Grossin, D.; and Ferrato, M.\n\n\n \n \n \n \n Experimental and numerical study for direct powder bed selective laser processing (sintering/melting) of silicon carbide ceramic.\n \n \n \n\n\n \n\n\n\n Materials Research Express, 8(4): 045603. April 2021.\n Publisher: IOP Publishing\n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{monton_experimental_2021,\n\ttitle = {Experimental and numerical study for direct powder bed selective laser processing (sintering/melting) of silicon carbide ceramic},\n\tvolume = {8},\n\tissn = {2053-1591},\n\tdoi = {10.1088/2053-1591/abf6fc},\n\tabstract = {The study was carried out to investigate the manufacturing possibility of Silicon Carbide (SiC) by direct Powder Bed Selective Laser Processing (PBSLP) experimentally and numerically. The experimental study was carried out by means of PBSLP while the numerical study was accomplished by developing a CFD model. The CFD model simulates accurately realistic conditions of the PBSLP process. A user-defined code, that describes the process parameters such as laser power, scanning speed, scanning strategies, and hatching distance has been developed and compiled to ANSYS FLUENT 2020 R1. Also, the model was validated with the available published data from the literature. The model was used to deeply analyse and support the results obtained through the experimental runs. Different values of laser power and scanning speeds with scanning strategy in the form of a continuous linear pattern and rotated by 90 degrees between layers were studied. The laser power is ranging from 52W to 235 W while the scanning speed is ranging from 300 to 3900 mm s−1. The results showed that the direct PBSLP of SiC is possible with the optimization of the process parameters. Layer thickness and hatching distance are the most important parameters that needed to be optimized. Also, the laser power and scanning speed needed to be adjusted so that the scanning temperature was between the sintering and the decomposition limits. The good agreement between experimental and simulation results proved the power and ability of the developed CFD model to be a useful tool to analyse and optimize future experimental data.},\n\tlanguage = {en},\n\tnumber = {4},\n\turldate = {2023-10-28},\n\tjournal = {Materials Research Express},\n\tauthor = {Montón, Alejandro and Abdelmoula, Mohammed and Küçüktürk, Gökhan and Maury, Francis and Grossin, David and Ferrato, Marc},\n\tmonth = apr,\n\tyear = {2021},\n\tnote = {Publisher: IOP Publishing},\n\tpages = {045603},\n}\n\n\n\n\n\n\n\n\n\n\n\n
\n
\n\n\n
\n The study was carried out to investigate the manufacturing possibility of Silicon Carbide (SiC) by direct Powder Bed Selective Laser Processing (PBSLP) experimentally and numerically. The experimental study was carried out by means of PBSLP while the numerical study was accomplished by developing a CFD model. The CFD model simulates accurately realistic conditions of the PBSLP process. A user-defined code, that describes the process parameters such as laser power, scanning speed, scanning strategies, and hatching distance has been developed and compiled to ANSYS FLUENT 2020 R1. Also, the model was validated with the available published data from the literature. The model was used to deeply analyse and support the results obtained through the experimental runs. Different values of laser power and scanning speeds with scanning strategy in the form of a continuous linear pattern and rotated by 90 degrees between layers were studied. The laser power is ranging from 52W to 235 W while the scanning speed is ranging from 300 to 3900 mm s−1. The results showed that the direct PBSLP of SiC is possible with the optimization of the process parameters. Layer thickness and hatching distance are the most important parameters that needed to be optimized. Also, the laser power and scanning speed needed to be adjusted so that the scanning temperature was between the sintering and the decomposition limits. The good agreement between experimental and simulation results proved the power and ability of the developed CFD model to be a useful tool to analyse and optimize future experimental data.\n
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\n \n\n \n \n Mostafaei, A.; Elliott, A. M.; Barnes, J. E.; Li, F.; Tan, W.; Cramer, C. L.; Nandwana, P.; and Chmielus, M.\n\n\n \n \n \n \n \n Binder jet 3D printing—Process parameters, materials, properties, modeling, and challenges.\n \n \n \n \n\n\n \n\n\n\n Progress in Materials Science, 119: 100707. June 2021.\n \n\n\n\n
\n\n\n\n \n \n \"BinderPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{mostafaei_binder_2021,\n\ttitle = {Binder jet {3D} printing—{Process} parameters, materials, properties, modeling, and challenges},\n\tvolume = {119},\n\tissn = {0079-6425},\n\turl = {https://www.sciencedirect.com/science/article/pii/S0079642520300712},\n\tdoi = {10.1016/j.pmatsci.2020.100707},\n\tabstract = {As a non-beam-based additive manufacturing (AM) method, binder jet 3D printing (BJ3DP) is a process in which a liquid binder is jetted on layers of powdered materials, selectively joined, and then followed by densification process. Among AM technologies, binder jetting holds distinctive promise because of the possibility of rapid production of complex structures to achieve isotropic properties in the 3D printed samples. By taking advantage of traditional powder metallurgy, BJ3DP machines can produce prototypes in which material properties and surface finish are similar to those attained with traditional powder metallurgy. Various powdered materials have been 3D printed, but a typical challenge during BJ3DP is developing printing and post-processing methods that maximize part performance. Therefore, a detailed review of the physical processes during 3D printing and the fundamental science of densification after sintering and post–heat treatment steps are provided to understand the microstructural evolution and properties of binder jetted parts. Furthermore, to determine the effects of the binder jetting process on metallurgical properties, the role of powder characteristics (e.g., morphology, mean size, distribution), printing process parameters (e.g., layer thickness, print orientation, binder saturation, print speed, drying time), sintering (e.g., temperature, holding time), and post-processing are discussed. With the development of AM technologies and the need for post-processing in 3D printed parts, understanding the microstructural evolution during densification is necessary and here, processing steps are explained. Finally, opportunities for future advancement are addressed.},\n\turldate = {2023-10-28},\n\tjournal = {Progress in Materials Science},\n\tauthor = {Mostafaei, Amir and Elliott, Amy M. and Barnes, John E. and Li, Fangzhou and Tan, Wenda and Cramer, Corson L. and Nandwana, Peeyush and Chmielus, Markus},\n\tmonth = jun,\n\tyear = {2021},\n\tkeywords = {Additive manufacturing, Binder, Ceramic, Composite, Indirect 3D printing, Infiltration, Materials selection, Metal, Post-processing, Powder bed, Powder characteristics, Print processing parameters, Sintering},\n\tpages = {100707},\n}\n\n\n\n
\n
\n\n\n
\n As a non-beam-based additive manufacturing (AM) method, binder jet 3D printing (BJ3DP) is a process in which a liquid binder is jetted on layers of powdered materials, selectively joined, and then followed by densification process. Among AM technologies, binder jetting holds distinctive promise because of the possibility of rapid production of complex structures to achieve isotropic properties in the 3D printed samples. By taking advantage of traditional powder metallurgy, BJ3DP machines can produce prototypes in which material properties and surface finish are similar to those attained with traditional powder metallurgy. Various powdered materials have been 3D printed, but a typical challenge during BJ3DP is developing printing and post-processing methods that maximize part performance. Therefore, a detailed review of the physical processes during 3D printing and the fundamental science of densification after sintering and post–heat treatment steps are provided to understand the microstructural evolution and properties of binder jetted parts. Furthermore, to determine the effects of the binder jetting process on metallurgical properties, the role of powder characteristics (e.g., morphology, mean size, distribution), printing process parameters (e.g., layer thickness, print orientation, binder saturation, print speed, drying time), sintering (e.g., temperature, holding time), and post-processing are discussed. With the development of AM technologies and the need for post-processing in 3D printed parts, understanding the microstructural evolution during densification is necessary and here, processing steps are explained. Finally, opportunities for future advancement are addressed.\n
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\n \n\n \n \n Koyanagi, T.; Terrani, K.; Harrison, S.; Liu, J.; and Katoh, Y.\n\n\n \n \n \n \n \n Additive manufacturing of silicon carbide for nuclear applications.\n \n \n \n \n\n\n \n\n\n\n Journal of Nuclear Materials, 543: 152577. January 2021.\n \n\n\n\n
\n\n\n\n \n \n \"AdditivePaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{koyanagi_additive_2021,\n\ttitle = {Additive manufacturing of silicon carbide for nuclear applications},\n\tvolume = {543},\n\tissn = {0022-3115},\n\turl = {https://www.sciencedirect.com/science/article/pii/S0022311520311855},\n\tdoi = {10.1016/j.jnucmat.2020.152577},\n\tabstract = {Additive manufacturing (AM) is a rapidly evolving technology being considered for nuclear applications. A special focus on AM to fabricate nuclear-grade silicon carbide (SiC) is explored in this paper. First, we present currently available AM processing options for SiC. AM methods commonly used for other ceramics, in which the feedstocks are forms of polymers, powders, and/or reactive chemical vapors, are also applicable to SiC. SiC phases are formed by pyrolysis of pre-ceramic polymer, direct reaction of powder precursors, sintering of SiC powders, or chemical vapor deposition/infiltration. Second, we discuss how the different microstructures of SiC materials fabricated by various processing methods affect their behavior in nuclear environments. Third, we discuss state-of-the-art AM technologies for the fabrication of relatively pure SiC, which show great potential to retain its strength under neutron irradiation: (1) binder jet printing followed by chemical vapor infiltration, (2) laser chemical vapor deposition, and (3) selective laser sintering of SiC powders.},\n\turldate = {2023-10-28},\n\tjournal = {Journal of Nuclear Materials},\n\tauthor = {Koyanagi, Takaaki and Terrani, Kurt and Harrison, Shay and Liu, Jian and Katoh, Yutai},\n\tmonth = jan,\n\tyear = {2021},\n\tkeywords = {Silicon carbide, additive manufacturing, microstructure, neutron irradiation, swelling},\n\tpages = {152577},\n}\n\n\n\n
\n
\n\n\n
\n Additive manufacturing (AM) is a rapidly evolving technology being considered for nuclear applications. A special focus on AM to fabricate nuclear-grade silicon carbide (SiC) is explored in this paper. First, we present currently available AM processing options for SiC. AM methods commonly used for other ceramics, in which the feedstocks are forms of polymers, powders, and/or reactive chemical vapors, are also applicable to SiC. SiC phases are formed by pyrolysis of pre-ceramic polymer, direct reaction of powder precursors, sintering of SiC powders, or chemical vapor deposition/infiltration. Second, we discuss how the different microstructures of SiC materials fabricated by various processing methods affect their behavior in nuclear environments. Third, we discuss state-of-the-art AM technologies for the fabrication of relatively pure SiC, which show great potential to retain its strength under neutron irradiation: (1) binder jet printing followed by chemical vapor infiltration, (2) laser chemical vapor deposition, and (3) selective laser sintering of SiC powders.\n
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\n\n\n
\n \n\n \n \n He, R.; Zhou, N.; Zhang, K.; Zhang, X.; Zhang, L.; Wang, W.; and Fang, D.\n\n\n \n \n \n \n Progress and challenges towards additive manufacturing of SiC ceramic.\n \n \n \n\n\n \n\n\n\n Journal of Advanced Ceramics, 10(4): 637–674. August 2021.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{he_progress_2021,\n\ttitle = {Progress and challenges towards additive manufacturing of {SiC} ceramic},\n\tvolume = {10},\n\tissn = {2227-8508},\n\tdoi = {10.1007/s40145-021-0484-z},\n\tabstract = {Silicon carbide (SiC) ceramic and related materials are widely used in various military and engineering fields. The emergence of additive manufacturing (AM) technologies provides a new approach for the fabrication of SiC ceramic products. This article systematically reviews the additive manufacturing technologies of SiC ceramic developed in recent years, including Indirect Additive Manufacturing (Indirect AM) and Direct Additive Manufacturing (Direct AM) technologies. This review also summarizes the key scientific and technological challenges for the additive manufacturing of SiC ceramic, and also forecasts its possible future opportunities. This paper aims to provide a helpful guidance for the additive manufacturing of SiC ceramic and other structural ceramics.},\n\tlanguage = {en},\n\tnumber = {4},\n\turldate = {2023-10-28},\n\tjournal = {Journal of Advanced Ceramics},\n\tauthor = {He, Rujie and Zhou, Niping and Zhang, Keqiang and Zhang, Xueqin and Zhang, Lu and Wang, Wenqing and Fang, Daining},\n\tmonth = aug,\n\tyear = {2021},\n\tkeywords = {additive manufacturing (AM), silicon carbide (SiC), structural ceramics},\n\tpages = {637--674},\n}\n\n\n\n\n\n\n\n\n\n\n\n
\n
\n\n\n
\n Silicon carbide (SiC) ceramic and related materials are widely used in various military and engineering fields. The emergence of additive manufacturing (AM) technologies provides a new approach for the fabrication of SiC ceramic products. This article systematically reviews the additive manufacturing technologies of SiC ceramic developed in recent years, including Indirect Additive Manufacturing (Indirect AM) and Direct Additive Manufacturing (Direct AM) technologies. This review also summarizes the key scientific and technological challenges for the additive manufacturing of SiC ceramic, and also forecasts its possible future opportunities. This paper aims to provide a helpful guidance for the additive manufacturing of SiC ceramic and other structural ceramics.\n
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\n \n\n \n \n Grover, M. S.; and Valentini, P.\n\n\n \n \n \n \n Ab initio simulation of hypersonic flows past a cylinder based on accurate potential energy surfaces.\n \n \n \n\n\n \n\n\n\n Physics of Fluids, 33(5): 051704. May 2021.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{grover2021,\n\ttitle = {\\textit{{Ab} initio} simulation of hypersonic flows past a cylinder based on accurate potential energy surfaces},\n\tvolume = {33},\n\tissn = {1070-6631, 1089-7666},\n\tdoi = {10.1063/5.0047945},\n\tabstract = {For the first time in the literature, we present 2D simulations of hypersonic flows around a cylinder obtained from accurate ab initio potential energy surfaces (PESs). We compare results obtained from a low fidelity (empirical) and a high fidelity (ab initio) PES, thus demonstrating the impact of PES accuracy on the entire aerothermodynamic field around the body. We observe that the empirical PES is not adequate to accurately reproduce rotational and vibrational relaxation in the hypersonic flow, both in the compression and expansion regions of the flow field. This approach, enabled by advancements in large-scale computing, paves the way to the direct simulation of hypersonic flows where the only modeling input is the PES that describes molecular interactions between the various air constituents. Such flow field simulations provide benchmark solutions for the validation of reduced-order models.},\n\tlanguage = {en},\n\tnumber = {5},\n\turldate = {2023-09-08},\n\tjournal = {Physics of Fluids},\n\tauthor = {Grover, Maninder S. and Valentini, Paolo},\n\tmonth = may,\n\tyear = {2021},\n\tpages = {051704},\n}\n\n\n\n\n\n\n\n
\n
\n\n\n
\n For the first time in the literature, we present 2D simulations of hypersonic flows around a cylinder obtained from accurate ab initio potential energy surfaces (PESs). We compare results obtained from a low fidelity (empirical) and a high fidelity (ab initio) PES, thus demonstrating the impact of PES accuracy on the entire aerothermodynamic field around the body. We observe that the empirical PES is not adequate to accurately reproduce rotational and vibrational relaxation in the hypersonic flow, both in the compression and expansion regions of the flow field. This approach, enabled by advancements in large-scale computing, paves the way to the direct simulation of hypersonic flows where the only modeling input is the PES that describes molecular interactions between the various air constituents. Such flow field simulations provide benchmark solutions for the validation of reduced-order models.\n
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\n \n\n \n \n Streicher, J. W.; Krish, A.; and Hanson, R. K.\n\n\n \n \n \n \n \n Coupled vibration-dissociation time-histories and rate measurements in shock-heated, nondilute O2 and O2–Ar mixtures from 6000 to 14 000 K.\n \n \n \n \n\n\n \n\n\n\n Physics of Fluids, 33(5): 056107. May 2021.\n \n\n\n\n
\n\n\n\n \n \n \"CoupledPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{streicher2021,\n\ttitle = {Coupled vibration-dissociation time-histories and rate measurements in shock-heated, nondilute {O2} and {O2}–{Ar} mixtures from 6000 to 14 000 {K}},\n\tvolume = {33},\n\tissn = {1070-6631},\n\turl = {https://doi.org/10.1063/5.0048059},\n\tdoi = {10.1063/5.0048059},\n\tabstract = {Validation of high-fidelity models for high-temperature hypersonic flows requires high-accuracy kinetics data for oxygen (O2) reactions, including time-histories and rate parameter measurements. Consequently, shock-tube experiments with ultraviolet (UV) laser absorption were performed to measure quantum-state-specific time-histories and coupled vibration-dissociation (CVDV) rate parameters in shock-heated, nondilute O2 and oxygen–argon (O2–Ar) mixtures. Experiments probed mixtures of 20\\% O2–Ar, 50\\% O2–Ar, and 100\\% O2 for initial post-reflected-shock conditions from 6000 to 14 000 K and 26–210 Torr. Two UV lasers—one continuous-wave laser and one pulsed laser—measured absorbance time-histories from the fifth and sixth vibrational levels of the electronic ground state of O2, respectively. The absorbance time-histories subsequently yielded time-histories for vibrational temperature (Tv) from the absorbance ratio, translational/rotational temperature (Ttr) from energy conservation, total O2 number density (nO2) from the individual absorbances, and vibrational-state-specific number density (nv″) from the Boltzmann population fractions. These state-specific temperature and number density time-histories demonstrate the low uncertainty necessary for high-temperature model validation and provide data to higher temperature than previous experiments. Additional analysis of the temperature and number density time-histories allowed inference of rate parameters in the Marrone and Treanor CVDV model, including vibrational relaxation time (τO2−O2), average vibrational energy loss (ε), vibrational coupling factor (Z), and dissociation rate constants (kdO2−O2 and kdO2−O). The results for each of these five parameters show reasonable consistency across the range of temperatures, pressures, and mixtures and generally agree with a modified Marrone and Treanor model by Chaudhry et al. [“Implementation of a chemical kinetics model for hypersonic flows in air for high-performance CFD,” in Proceedings of AIAA Scitech Forum (2020)]. Finally, the results for τO2−O2, kdO2−O2, and kdO2−O exhibit much lower scatter than previous experimental studies.},\n\tnumber = {5},\n\turldate = {2023-08-10},\n\tjournal = {Physics of Fluids},\n\tauthor = {Streicher, Jesse W. and Krish, Ajay and Hanson, Ronald K.},\n\tmonth = may,\n\tyear = {2021},\n\tpages = {056107},\n}\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n
\n
\n\n\n
\n Validation of high-fidelity models for high-temperature hypersonic flows requires high-accuracy kinetics data for oxygen (O2) reactions, including time-histories and rate parameter measurements. Consequently, shock-tube experiments with ultraviolet (UV) laser absorption were performed to measure quantum-state-specific time-histories and coupled vibration-dissociation (CVDV) rate parameters in shock-heated, nondilute O2 and oxygen–argon (O2–Ar) mixtures. Experiments probed mixtures of 20% O2–Ar, 50% O2–Ar, and 100% O2 for initial post-reflected-shock conditions from 6000 to 14 000 K and 26–210 Torr. Two UV lasers—one continuous-wave laser and one pulsed laser—measured absorbance time-histories from the fifth and sixth vibrational levels of the electronic ground state of O2, respectively. The absorbance time-histories subsequently yielded time-histories for vibrational temperature (Tv) from the absorbance ratio, translational/rotational temperature (Ttr) from energy conservation, total O2 number density (nO2) from the individual absorbances, and vibrational-state-specific number density (nv″) from the Boltzmann population fractions. These state-specific temperature and number density time-histories demonstrate the low uncertainty necessary for high-temperature model validation and provide data to higher temperature than previous experiments. Additional analysis of the temperature and number density time-histories allowed inference of rate parameters in the Marrone and Treanor CVDV model, including vibrational relaxation time (τO2−O2), average vibrational energy loss (ε), vibrational coupling factor (Z), and dissociation rate constants (kdO2−O2 and kdO2−O). The results for each of these five parameters show reasonable consistency across the range of temperatures, pressures, and mixtures and generally agree with a modified Marrone and Treanor model by Chaudhry et al. [“Implementation of a chemical kinetics model for hypersonic flows in air for high-performance CFD,” in Proceedings of AIAA Scitech Forum (2020)]. Finally, the results for τO2−O2, kdO2−O2, and kdO2−O exhibit much lower scatter than previous experimental studies.\n
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\n \n\n \n \n Neely, A.\n\n\n \n \n \n \n \n High-Speed FSI Databases - Unit Cases.\n \n \n \n \n\n\n \n\n\n\n UNSW Canberra. 2021.\n \n\n\n\n
\n\n\n\n \n \n \"High-SpeedPaper\n  \n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{neely2021,\n\ttitle = {High-{Speed} {FSI} {Databases} - {Unit} {Cases}},\n\turl = {https://www.unsw.adfa.edu.au/high-speed-fsi-database-unit-cases},\n\tjournal = {UNSW Canberra},\n\tauthor = {Neely, Andrew},\n\tyear = {2021},\n}\n\n\n\n
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\n \n\n \n \n Sasidharan, V.; and Duvvuri, S.\n\n\n \n \n \n \n Large- and small-amplitude shock-wave oscillations over axisymmetric bodies in high-speed flow.\n \n \n \n\n\n \n\n\n\n Journal of Fluid Mechanics, 913. 2021.\n Publisher: Cambridge University Press\n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n\n\n\n
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@article{sasidharan2021,\n\ttitle = {Large- and small-amplitude shock-wave oscillations over axisymmetric bodies in high-speed flow},\n\tvolume = {913},\n\tdoi = {10.1017/JFM.2021.115},\n\tabstract = {The phenomena of self-sustained shock-wave oscillations over conical bodies with a blunt axisymmetric base subject to uniform high-speed flow are investigated in a hypersonic wind tunnel at Mach number . The flow and shock-wave dynamics is dictated by two non-dimensional geometric parameters presented by the three length scales of the body, two of which are associated with the conical forebody and one with the base. Time-resolved schlieren imagery from these experiments reveals the presence of two disparate states of shock-wave oscillations in the flow, and allows for the mapping of unsteadiness boundaries in the two-parameter space. Physical mechanisms are proposed to explain the oscillations and the transitions of the shock-wave system from steady to oscillatory states. In comparison with the canonical single-parameter problem of shock-wave oscillations over spiked-blunt bodies reported in literature, the two-parameter nature of the present problem introduces distinct elements to the flow dynamics.},\n\tjournal = {Journal of Fluid Mechanics},\n\tauthor = {Sasidharan, Vaisakh and Duvvuri, Subrahmanyam},\n\tyear = {2021},\n\tnote = {Publisher: Cambridge University Press},\n\tkeywords = {high-speed flow, shock waves},\n}\n\n\n\n
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\n The phenomena of self-sustained shock-wave oscillations over conical bodies with a blunt axisymmetric base subject to uniform high-speed flow are investigated in a hypersonic wind tunnel at Mach number . The flow and shock-wave dynamics is dictated by two non-dimensional geometric parameters presented by the three length scales of the body, two of which are associated with the conical forebody and one with the base. Time-resolved schlieren imagery from these experiments reveals the presence of two disparate states of shock-wave oscillations in the flow, and allows for the mapping of unsteadiness boundaries in the two-parameter space. Physical mechanisms are proposed to explain the oscillations and the transitions of the shock-wave system from steady to oscillatory states. In comparison with the canonical single-parameter problem of shock-wave oscillations over spiked-blunt bodies reported in literature, the two-parameter nature of the present problem introduces distinct elements to the flow dynamics.\n
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\n \n\n \n \n Sadagopan, A.; Huang, D.; Martin, L. E.; and Hanquist, K. M.\n\n\n \n \n \n \n Assessment of High-Temperature Effects on Hypersonic Aerothermoelastic Analysis using Multi-Fidelity Multi-Variate Surrogates.\n \n \n \n\n\n \n\n\n\n In January 2021. AIAA Paper 2021-1610\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n  \n \n 6 downloads\n \n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@inproceedings{sadagopan2021,\n\ttitle = {Assessment of {High}-{Temperature} {Effects} on {Hypersonic} {Aerothermoelastic} {Analysis} using {Multi}-{Fidelity} {Multi}-{Variate} {Surrogates}},\n\tisbn = {978-1-62410-609-5},\n\tdoi = {10.2514/6.2021-1610},\n\tabstract = {This study investigates the impact of the high-temperature effect, esp. the real gas effect and the chemical reactions, on hypersonic aerothermodynamic solutions of double cone and double wedge configurations, as well as the aerothermoelastic behavior of a double wedge configuration in hypersonic flow. First, a high-temperature computational fluid dynamics code was benchmarked and correlated with experimental results, emphasizing the impact of high-temperature effects as well as turbulence modeling on heat flux prediction. Subsequently, an aerothermal surrogate based on the multi-fidelity Gaussian process regression method was developed. The model achieves a balance between model accuracy and computational cost of sample generation, using the combination of a few high-fidelity sample and many low-fidelity samples. Finally, the new aerothermal surrogate was applied to study the impact of the high-temperature effect on the aerothermoelastic response of a hypersonic skin panel, emphasizing the necessity of the accurate characterization of the localized heat flux for reasonable assessment of the response of a compliant structure in high-speed high-temperature flowfield.},\n\tpublisher = {AIAA Paper 2021-1610},\n\tauthor = {Sadagopan, Aravinth and Huang, Daning and Martin, Liza E. and Hanquist, Kyle M.},\n\tmonth = jan,\n\tyear = {2021},\n}\n\n\n\n
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\n This study investigates the impact of the high-temperature effect, esp. the real gas effect and the chemical reactions, on hypersonic aerothermodynamic solutions of double cone and double wedge configurations, as well as the aerothermoelastic behavior of a double wedge configuration in hypersonic flow. First, a high-temperature computational fluid dynamics code was benchmarked and correlated with experimental results, emphasizing the impact of high-temperature effects as well as turbulence modeling on heat flux prediction. Subsequently, an aerothermal surrogate based on the multi-fidelity Gaussian process regression method was developed. The model achieves a balance between model accuracy and computational cost of sample generation, using the combination of a few high-fidelity sample and many low-fidelity samples. Finally, the new aerothermal surrogate was applied to study the impact of the high-temperature effect on the aerothermoelastic response of a hypersonic skin panel, emphasizing the necessity of the accurate characterization of the localized heat flux for reasonable assessment of the response of a compliant structure in high-speed high-temperature flowfield.\n
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\n \n\n \n \n Tang, X.; Kuehster, A. E.; DeBoer, B. A.; Preston, A. D.; and Ma, K.\n\n\n \n \n \n \n Enhanced thermionic emission of mayenite electride composites in an Ar glow discharge plasma.\n \n \n \n\n\n \n\n\n\n Ceramics International, 47(12): 16614–16631. June 2021.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n\n\n\n
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@article{tang2021,\n\ttitle = {Enhanced thermionic emission of mayenite electride composites in an {Ar} glow discharge plasma},\n\tvolume = {47},\n\tissn = {0272-8842},\n\tdoi = {10.1016/j.ceramint.2021.02.233},\n\tabstract = {Mayenite electride has attracted increasing research interests because of its unique electronic properties. The thermionic emission behavior of the mayenite electride is relatively unknown. Previous studies revealed that mayenite electride exhibited a bare work function ranged from 2.1–2.6 eV when the thermionic emission was tested in vacuum, and enhanced emission currents could be achieved by applying a super-high external electric field. In this paper, the thermionic emission behavior and the corresponding effective work function of two types of mayenite electride based composites, mayenite electride-titanium and mayenite electride-carbon, were investigated in an Ar glow discharge plasma at elevated temperatures (400–1000 K) without applying a high external electric field, which is critical for the application in electric propulsion and other aerospace apparatus, yet never had been done before. During the testing, the thermal equilibrium process and plasma sheath expansion were observed. The effective work function of the two mayenite electride composites were determined as a function of temperature. The Rasor-Warner model was applied to determine the bare work function and adsorption-site density of the mayenite electride based composites. Results suggested that the adsorption of Ar ions led to the enhanced thermionic emission ({\\textasciitilde}30 A/m2 at 985 K) and low effective work functions (0.9–2.2 eV) of mayenite electride based composites, without the need of applying high electric fields. Our findings will pave the ways for the application of mayenite electride and its composites as the thrust cathode materials for electric propulsion where plasma is present.},\n\tlanguage = {en},\n\tnumber = {12},\n\turldate = {2023-07-05},\n\tjournal = {Ceramics International},\n\tauthor = {Tang, Xiaochuan and Kuehster, Adam E. and DeBoer, Brodderic A. and Preston, Alexander D. and Ma, Kaka},\n\tmonth = jun,\n\tyear = {2021},\n\tkeywords = {Effective work function, Glow discharge plasma, Mayenite electride, Thermionic emission},\n\tpages = {16614--16631},\n}\n\n\n\n\n\n\n\n\n\n\n\n
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\n Mayenite electride has attracted increasing research interests because of its unique electronic properties. The thermionic emission behavior of the mayenite electride is relatively unknown. Previous studies revealed that mayenite electride exhibited a bare work function ranged from 2.1–2.6 eV when the thermionic emission was tested in vacuum, and enhanced emission currents could be achieved by applying a super-high external electric field. In this paper, the thermionic emission behavior and the corresponding effective work function of two types of mayenite electride based composites, mayenite electride-titanium and mayenite electride-carbon, were investigated in an Ar glow discharge plasma at elevated temperatures (400–1000 K) without applying a high external electric field, which is critical for the application in electric propulsion and other aerospace apparatus, yet never had been done before. During the testing, the thermal equilibrium process and plasma sheath expansion were observed. The effective work function of the two mayenite electride composites were determined as a function of temperature. The Rasor-Warner model was applied to determine the bare work function and adsorption-site density of the mayenite electride based composites. Results suggested that the adsorption of Ar ions led to the enhanced thermionic emission (~30 A/m2 at 985 K) and low effective work functions (0.9–2.2 eV) of mayenite electride based composites, without the need of applying high electric fields. Our findings will pave the ways for the application of mayenite electride and its composites as the thrust cathode materials for electric propulsion where plasma is present.\n
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\n \n\n \n \n Footohi, P.; Mozzone, L.; Shkarayev, S. V.; and Hanquist, K. M.\n\n\n \n \n \n \n Wingtip Jets Effects on Flow Entrainment and Aerodynamic Loads.\n \n \n \n\n\n \n\n\n\n In AIAA AVIATION 2021 FORUM, 2021. AIAA Paper 2021-2812\n \n\n\n\n
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@inproceedings{footohi2021a,\n\ttitle = {Wingtip {Jets} {Effects} on {Flow} {Entrainment} and {Aerodynamic} {Loads}},\n\tdoi = {10.2514/6.2021-2812},\n\tbooktitle = {{AIAA} {AVIATION} 2021 {FORUM}},\n\tpublisher = {AIAA Paper 2021-2812},\n\tauthor = {Footohi, Parisa and Mozzone, Luciano and Shkarayev, Sergey V. and Hanquist, Kyle M.},\n\tyear = {2021},\n\tdoi = {10.2514/6.2021-2812},\n\tkeywords = {Aerodynamic Force Coefficients, Aspect Ratio, Computational Fluid Dynamics Simulation, Data Acquisition, Internal Flows, Lift Coefficient, NACA 0012, Pressure Coefficient, Wind Tunnel Models, Wingtip Vortices, own},\n}\n\n\n\n
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\n \n\n \n \n Gross, A.; Castillo Gomez, P.; and Lee, S.\n\n\n \n \n \n \n Wall-Modeled Large-Eddy Simulations of Turbulent Shockwave Boundary Layer Interaction and Boundary Layer Flows.\n \n \n \n\n\n \n\n\n\n In AIAA AVIATION 2021 FORUM, VIRTUAL EVENT, August 2021. AIAA Paper 2021-2749\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@inproceedings{gross2021,\n\taddress = {VIRTUAL EVENT},\n\ttitle = {Wall-{Modeled} {Large}-{Eddy} {Simulations} of {Turbulent} {Shockwave} {Boundary} {Layer} {Interaction} and {Boundary} {Layer} {Flows}},\n\tisbn = {978-1-62410-610-1},\n\tdoi = {10.2514/6.2021-2749},\n\tlanguage = {en},\n\turldate = {2023-01-12},\n\tbooktitle = {{AIAA} {AVIATION} 2021 {FORUM}},\n\tpublisher = {AIAA Paper 2021-2749},\n\tauthor = {Gross, Andreas and Castillo Gomez, Pedro and Lee, Sunyoung},\n\tmonth = aug,\n\tyear = {2021},\n}\n\n\n\n
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\n \n\n \n \n Gallis, M. A.; Torczynski, J. R.; Krygier, M. C.; Bitter, N. P.; and Plimpton, S. J.\n\n\n \n \n \n \n Turbulence at the edge of continuum.\n \n \n \n\n\n \n\n\n\n Physical Review Fluids, 6(1): 013401. January 2021.\n \n\n\n\n
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@article{gallis2021a,\n\ttitle = {Turbulence at the edge of continuum},\n\tvolume = {6},\n\tissn = {2469-990X},\n\tdoi = {10.1103/PhysRevFluids.6.013401},\n\tlanguage = {en},\n\tnumber = {1},\n\turldate = {2023-01-12},\n\tjournal = {Physical Review Fluids},\n\tauthor = {Gallis, M. A. and Torczynski, J. R. and Krygier, M. C. and Bitter, N. P. and Plimpton, S. J.},\n\tmonth = jan,\n\tyear = {2021},\n\tpages = {013401},\n}\n\n\n\n
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\n \n\n \n \n Hanquist, K. M.\n\n\n \n \n \n \n Thermal Management of Hot Aerospace Surfaces using Plasma Assisted Cooling.\n \n \n \n\n\n \n\n\n\n 2021.\n \n\n\n\n
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@misc{hanquist2021,\n\taddress = {Department of Mechanical Engineering, University of Kentucky},\n\ttype = {Invited {Seminar}},\n\ttitle = {Thermal {Management} of {Hot} {Aerospace} {Surfaces} using {Plasma} {Assisted} {Cooling}},\n\tauthor = {Hanquist, Kyle M.},\n\tyear = {2021},\n\tkeywords = {invited, own},\n}\n\n\n\n
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\n \n\n \n \n Garbacz, C.; Morgado, F.; Fossati, M.; Maier, W. T; Needels, J.; Alonso, J. J.; Capitelli, M.; Scoggins, J. B.; Magin, T. E.; Liza, M. E.; and Hanquist, K. M.\n\n\n \n \n \n \n SU2-NEMO: An Open-Source Framework for Nonequilibrium Flows.\n \n \n \n\n\n \n\n\n\n 2021.\n \n\n\n\n
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@misc{garbacz2021,\n\taddress = {SU2 Conference 2021},\n\ttitle = {{SU2}-{NEMO}: {An} {Open}-{Source} {Framework} for {Nonequilibrium} {Flows}},\n\tauthor = {Garbacz, Catrina and Morgado, Fabio and Fossati, Marco and Maier, Walter T and Needels, Jacob and Alonso, Juan J. and Capitelli, M. and Scoggins, James B. and Magin, Thierry E. and Liza, Martin E. and Hanquist, Kyle M.},\n\tyear = {2021},\n\tkeywords = {own, presentation},\n}\n\n\n\n
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\n \n\n \n \n Maier, W. T.; Needels, J. T.; Garbacz, C.; Morgado, F.; Alonso, J. J.; and Fossati, M.\n\n\n \n \n \n \n \n SU2-NEMO: An Open-Source Framework for High-Mach Nonequilibrium Multi-Species Flows.\n \n \n \n \n\n\n \n\n\n\n Aerospace 2021, Vol. 8, Page 193, 8(7): 193–193. July 2021.\n Publisher: Multidisciplinary Digital Publishing Institute\n\n\n\n
\n\n\n\n \n \n \"SU2-NEMO:Paper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
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@article{maier2021a,\n\ttitle = {{SU2}-{NEMO}: {An} {Open}-{Source} {Framework} for {High}-{Mach} {Nonequilibrium} {Multi}-{Species} {Flows}},\n\tvolume = {8},\n\turl = {https://www.mdpi.com/2226-4310/8/7/193/htm},\n\tdoi = {10.3390/AEROSPACE8070193},\n\tabstract = {SU2-NEMO, a recent extension of the open-source SU2 multiphysics suite’s set of physical models and code architecture, is presented with the aim of introducing its enhanced capabilities in addressing high-enthalpy and high-Mach number flows. This paper discusses the thermal nonequilibrium and finite-rate chemistry models adopted, including a link to the Mutation++ physio-chemical library. Further, the paper discusses how the software architecture has been designed to ensure modularity, incorporating the ability to introduce additional models in an efficient manner. A review of the numerical formulation and the discretization schemes utilized for the convective fluxes is also presented. Several test cases in two- and three-dimensions are examined for validation purposes and to illustrate the performance of the solver in addressing complex nonequilibrium flows.},\n\tnumber = {7},\n\tjournal = {Aerospace 2021, Vol. 8, Page 193},\n\tauthor = {Maier, Walter T. and Needels, Jacob T. and Garbacz, Catarina and Morgado, Fábio and Alonso, Juan J. and Fossati, Marco},\n\tmonth = jul,\n\tyear = {2021},\n\tnote = {Publisher: Multidisciplinary Digital Publishing Institute},\n\tkeywords = {aerothermodynamics, computational fluid dynamics, high, hypersonic flight, nonequilibrium flows, temperature effects},\n\tpages = {193--193},\n}\n\n\n\n
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\n SU2-NEMO, a recent extension of the open-source SU2 multiphysics suite’s set of physical models and code architecture, is presented with the aim of introducing its enhanced capabilities in addressing high-enthalpy and high-Mach number flows. This paper discusses the thermal nonequilibrium and finite-rate chemistry models adopted, including a link to the Mutation++ physio-chemical library. Further, the paper discusses how the software architecture has been designed to ensure modularity, incorporating the ability to introduce additional models in an efficient manner. A review of the numerical formulation and the discretization schemes utilized for the convective fluxes is also presented. Several test cases in two- and three-dimensions are examined for validation purposes and to illustrate the performance of the solver in addressing complex nonequilibrium flows.\n
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\n \n\n \n \n Maier, W. T.; Needels, J. T.; Garbacz, C.; Morgado, F.; Alonso, J. J.; and Fossati, M.\n\n\n \n \n \n \n SU2-NEMO: An Open-Source Framework for High-Mach Nonequilibrium Multi-Species Flows.\n \n \n \n\n\n \n\n\n\n Aerospace, 8(7): 193. 2021.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
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@article{maier2021,\n\ttitle = {{SU2}-{NEMO}: {An} {Open}-{Source} {Framework} for {High}-{Mach} {Nonequilibrium} {Multi}-{Species} {Flows}},\n\tvolume = {8},\n\tdoi = {10.3390/aerospace8070193},\n\tabstract = {SU2-NEMO, a recent extension of the open-source SU2 multiphysics suite’s set of physical models and code architecture, is presented with the aim of introducing its enhanced capabilities in addressing high-enthalpy and high-Mach number flows. This paper discusses the thermal nonequilibrium and finite-rate chemistry models adopted, including a link to the Mutation++ physio-chemical library. Further, the paper discusses how the software architecture has been designed to ensure modularity, incorporating the ability to introduce additional models in an efficient manner. A review of the numerical formulation and the discretization schemes utilized for the convective fluxes is also presented. Several test cases in two- and three-dimensions are examined for validation purposes and to illustrate the performance of the solver in addressing complex nonequilibrium flows.},\n\tlanguage = {en},\n\tnumber = {7},\n\turldate = {2023-05-04},\n\tjournal = {Aerospace},\n\tauthor = {Maier, Walter T. and Needels, Jacob T. and Garbacz, Catarina and Morgado, Fábio and Alonso, Juan J. and Fossati, Marco},\n\tyear = {2021},\n\tkeywords = {aerothermodynamics, computational fluid dynamics, high-temperature effects, hypersonic flight, nonequilibrium flows},\n\tpages = {193},\n}\n\n\n\n
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\n SU2-NEMO, a recent extension of the open-source SU2 multiphysics suite’s set of physical models and code architecture, is presented with the aim of introducing its enhanced capabilities in addressing high-enthalpy and high-Mach number flows. This paper discusses the thermal nonequilibrium and finite-rate chemistry models adopted, including a link to the Mutation++ physio-chemical library. Further, the paper discusses how the software architecture has been designed to ensure modularity, incorporating the ability to introduce additional models in an efficient manner. A review of the numerical formulation and the discretization schemes utilized for the convective fluxes is also presented. Several test cases in two- and three-dimensions are examined for validation purposes and to illustrate the performance of the solver in addressing complex nonequilibrium flows.\n
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\n \n\n \n \n Parent, B.; and Hanquist, K. M.\n\n\n \n \n \n \n Plasma Sheath Modelling for Computational Aerothermodynamics and Magnetohydrodynamics.\n \n \n \n\n\n \n\n\n\n International Journal of Computational Fluid Dynamics, 35(5): 331–348. 2021.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n  \n \n 1 download\n \n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
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@article{parent2021d,\n\ttitle = {Plasma {Sheath} {Modelling} for {Computational} {Aerothermodynamics} and {Magnetohydrodynamics}},\n\tvolume = {35},\n\tdoi = {10.1080/10618562.2021.1949456},\n\tabstract = {To date, plasma sheath effects have not been incorporated into most CFD simulations of magnetohydrodynamics (MHD) or aerothermodynamics due to the high computational costs involved. The accurate mo...},\n\tnumber = {5},\n\tjournal = {International Journal of Computational Fluid Dynamics},\n\tauthor = {Parent, Bernard and Hanquist, Kyle M.},\n\tyear = {2021},\n\tkeywords = {Plasma sheath, electron transpiration cooling, hypersonic flight, magnetohydrodynamics, own, re-entry flows},\n\tpages = {331--348},\n}\n\n\n\n
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\n To date, plasma sheath effects have not been incorporated into most CFD simulations of magnetohydrodynamics (MHD) or aerothermodynamics due to the high computational costs involved. The accurate mo...\n
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\n \n\n \n \n Campbell, M. F.; Celenza, T. J.; Schmitt, F.; Schwede, J. W.; and Bargatin, I.\n\n\n \n \n \n \n Progress Toward High Power Output in Thermionic Energy Converters.\n \n \n \n\n\n \n\n\n\n Advanced Science, 8(9). 2021.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n\n\n\n
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@article{campbell2021b,\n\ttitle = {Progress {Toward} {High} {Power} {Output} in {Thermionic} {Energy} {Converters}},\n\tvolume = {8},\n\tdoi = {10.1002/ADVS.202003812},\n\tabstract = {Thermionic energy converters are solid-state heat engines that have the potential to produce electricity with efficiencies of over 30\\% and area-specific power densities of 100 Wcm−2. Despite this prospect, no prototypes reported in the literature have achieved true efficiencies close to this target, and many of the most recent investigations report power densities on the order of mWcm−2 or less. These discrepancies stem in part from the low-temperature ({\\textless}1300 K) test conditions used to evaluate these devices, the large vacuum gap distances (25–100 µm) employed by these devices, and material challenges related to these devices' electrodes. This review will argue that, for feasible electrode work functions available today, efficient performance requires generating output power densities of {\\textgreater}1 Wcm−2 and employing emitter temperatures of 1300 K or higher. With this result in mind, this review provides an overview of historical and current design architectures and comments on their capacity to realize the efficiency and power potential of thermionic energy converters. Also emphasized is the importance of using standardized efficiency metrics to report thermionic energy converter performance data.},\n\tnumber = {9},\n\tjournal = {Advanced Science},\n\tauthor = {Campbell, Matthew F. and Celenza, Thomas J. and Schmitt, Felix and Schwede, Jared W. and Bargatin, Igor},\n\tyear = {2021},\n\tkeywords = {efficiency, heat transfer, power density, thermionic energy conversion},\n}\n\n\n\n
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\n Thermionic energy converters are solid-state heat engines that have the potential to produce electricity with efficiencies of over 30% and area-specific power densities of 100 Wcm−2. Despite this prospect, no prototypes reported in the literature have achieved true efficiencies close to this target, and many of the most recent investigations report power densities on the order of mWcm−2 or less. These discrepancies stem in part from the low-temperature (\\textless1300 K) test conditions used to evaluate these devices, the large vacuum gap distances (25–100 µm) employed by these devices, and material challenges related to these devices' electrodes. This review will argue that, for feasible electrode work functions available today, efficient performance requires generating output power densities of \\textgreater1 Wcm−2 and employing emitter temperatures of 1300 K or higher. With this result in mind, this review provides an overview of historical and current design architectures and comments on their capacity to realize the efficiency and power potential of thermionic energy converters. Also emphasized is the importance of using standardized efficiency metrics to report thermionic energy converter performance data.\n
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\n \n\n \n \n Bandari, A.\n\n\n \n \n \n \n \n Preventing a communication blackout in spacecraft during reentry.\n \n \n \n \n\n\n \n\n\n\n Scilight, 2021(10). March 2021.\n Publisher: AIP Publishing LLC AIP Publishing\n\n\n\n
\n\n\n\n \n \n \"PreventingPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{bandari2021,\n\ttitle = {Preventing a communication blackout in spacecraft during reentry},\n\tvolume = {2021},\n\turl = {https://aip.scitation.org/doi/abs/10.1063/10.0003770},\n\tdoi = {10.1063/10.0003770},\n\tabstract = {A two-layer metamaterial with optimized permeability and permittivity placed between the plasma surrounding an aircraft and an antenna located in its interior can help prevent radio wave attenuatio...},\n\tnumber = {10},\n\tjournal = {Scilight},\n\tauthor = {Bandari, Anashe},\n\tmonth = mar,\n\tyear = {2021},\n\tnote = {Publisher: AIP Publishing LLC AIP Publishing},\n}\n\n\n\n
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\n A two-layer metamaterial with optimized permeability and permittivity placed between the plasma surrounding an aircraft and an antenna located in its interior can help prevent radio wave attenuatio...\n
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\n \n\n \n \n Garbacz, C.; Morgado, F.; Fossati, M.; Maier, W. T.; Munguía, B. C.; Alonso, J. J.; and Loseille, A.\n\n\n \n \n \n \n Parametric study of nonequilibrium shock interference patterns over a fuselage-and-wing conceptual vehicle.\n \n \n \n\n\n \n\n\n\n AIAA Journal, 59(12): 4905–4916. December 2021.\n Publisher: AIAA International\n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{garbacz2021b,\n\ttitle = {Parametric study of nonequilibrium shock interference patterns over a fuselage-and-wing conceptual vehicle},\n\tvolume = {59},\n\tdoi = {10.2514/1.J060470},\n\tabstract = {Predicting shock/shock and shock/boundary-layer interactions in gas flows that surround high-speed vehicles is key in aerodynamic design. Under typical hypersonic conditions, these flow structures are influenced by complex nonequilibrium phenomena leading to high-temperature effects. In this work, the conceptual Bedford wing-body vehicle is studied to analyze flow patterns in shock/shock and shock/boundary-layer interactions with thermochemical nonequilibrium. A parametric computational fluid dynamics study is carried out for different hypersonic operating conditions, with respect to the freestream Mach number. Simulations are performed with the SU2-NEMO solver coupled to the Mutation++ library, which provides all the necessary thermodynamic, kinetic, and transport properties of the mixture and chemical species. The Adaptive Mesh Generation library is used for automatic anisotropic mesh adaptation. Numerical results show that increasing the freestream Mach number from 4 to 10 leads to changes in the shock layer, locations of shock impingement, and regions of boundary-layer separation. Despite these changes, the change in freestream Mach number has little impact on the overall shock interaction structures.},\n\tnumber = {12},\n\tjournal = {AIAA Journal},\n\tauthor = {Garbacz, Catarina and Morgado, Fábio and Fossati, Marco and Maier, Walter T. and Munguía, Brian C. and Alonso, Juan J. and Loseille, Adrien},\n\tmonth = dec,\n\tyear = {2021},\n\tnote = {Publisher: AIAA International},\n\tkeywords = {Aerodynamic Coefficients, Attached Shock Wave, Boundary Layer Interaction, CFD Simulation, High Lift Device, Lift Coefficient, Mesh Generation, Nonequilibrium Flows, Temperature Effects, Vibrational Energy},\n\tpages = {4905--4916},\n}\n\n\n\n
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\n Predicting shock/shock and shock/boundary-layer interactions in gas flows that surround high-speed vehicles is key in aerodynamic design. Under typical hypersonic conditions, these flow structures are influenced by complex nonequilibrium phenomena leading to high-temperature effects. In this work, the conceptual Bedford wing-body vehicle is studied to analyze flow patterns in shock/shock and shock/boundary-layer interactions with thermochemical nonequilibrium. A parametric computational fluid dynamics study is carried out for different hypersonic operating conditions, with respect to the freestream Mach number. Simulations are performed with the SU2-NEMO solver coupled to the Mutation++ library, which provides all the necessary thermodynamic, kinetic, and transport properties of the mixture and chemical species. The Adaptive Mesh Generation library is used for automatic anisotropic mesh adaptation. Numerical results show that increasing the freestream Mach number from 4 to 10 leads to changes in the shock layer, locations of shock impingement, and regions of boundary-layer separation. Despite these changes, the change in freestream Mach number has little impact on the overall shock interaction structures.\n
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\n \n\n \n \n Evans, J. V.; Senior, W. C.; Gejji, R. M.; Strahan, N. L.; and Slabaugh, C. D.\n\n\n \n \n \n \n \n Performance of an sfrj with an aft-mixing section utilizing bypass air.\n \n \n \n \n\n\n \n\n\n\n In pages 1–10, 2021. AIAA Paper 2021-1876\n \n\n\n\n
\n\n\n\n \n \n \"PerformancePaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{evans2021,\n\ttitle = {Performance of an sfrj with an aft-mixing section utilizing bypass air},\n\tisbn = {978-1-62410-609-5},\n\turl = {https://arc.aiaa.org/doi/10.2514/6.2021-1876},\n\tdoi = {10.2514/6.2021-1876},\n\tabstract = {The effect of secondary injection of air downstream of the combustor of a model solid-fuel ramjet (SFRJ) combustor on its global performance is studied. The SFRJ is operated with heated non-vitiated air (2 = 387-727 °F, = 2.31-3.81 lbm/s) and cylindrical, center-perforated HTPB fuel grains. The secondary air bypass ratio is varied from 0-30\\%. For comparable operating conditions, the use of the aft-mixing section (AMS) resulted in an improvement in combustion efficiency from ∼85\\% to ∼95\\% and increase in from ∼110 s to ∼130 s. The bypass air was introduced into the AMS using circumferential jet injection at momentum flux ratios of 3-3.5 and 20. For comparable operating conditions, the = 20 cases had a slightly lower combustion efficiency than the = 3-3.5 cases. The jet trajectory and heat-release in the AMS were characterized using broadband chemiluminescence performed at 6 kHz and CH* chemiluminescence performed at 50 kHz.},\n\tpublisher = {AIAA Paper 2021-1876},\n\tauthor = {Evans, Jay V. and Senior, William C.B. and Gejji, Rohan M. and Strahan, Nicholas L. and Slabaugh, Carson D.},\n\tyear = {2021},\n\tpages = {1--10},\n}\n\n\n\n
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\n The effect of secondary injection of air downstream of the combustor of a model solid-fuel ramjet (SFRJ) combustor on its global performance is studied. The SFRJ is operated with heated non-vitiated air (2 = 387-727 °F, = 2.31-3.81 lbm/s) and cylindrical, center-perforated HTPB fuel grains. The secondary air bypass ratio is varied from 0-30%. For comparable operating conditions, the use of the aft-mixing section (AMS) resulted in an improvement in combustion efficiency from ∼85% to ∼95% and increase in from ∼110 s to ∼130 s. The bypass air was introduced into the AMS using circumferential jet injection at momentum flux ratios of 3-3.5 and 20. For comparable operating conditions, the = 20 cases had a slightly lower combustion efficiency than the = 3-3.5 cases. The jet trajectory and heat-release in the AMS were characterized using broadband chemiluminescence performed at 6 kHz and CH* chemiluminescence performed at 50 kHz.\n
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\n \n\n \n \n Needels, J.; Gage, P.; and Hill, J.\n\n\n \n \n \n \n Interpretation of Vehicle Tumbling Predictions From 6-DOF Entry and Descent Simulation.\n \n \n \n\n\n \n\n\n\n In 2021. \n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{needels2021,\n\ttitle = {Interpretation of {Vehicle} {Tumbling} {Predictions} {From} 6-{DOF} {Entry} and {Descent} {Simulation}},\n\tauthor = {Needels, J. and Gage, P. and Hill, J.},\n\tyear = {2021},\n}\n\n\n\n
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\n \n\n \n \n Hanquist, K. M.\n\n\n \n \n \n \n Importance of Modeling in Hypersonic Flight Conditions.\n \n \n \n\n\n \n\n\n\n 2021.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n\n\n\n
\n 
@misc{hanquist2021a,\n\taddress = {Department of Aerospace \\& Mechanical Engineering, New Mexico State University},\n\ttype = {Invited {Seminar}},\n\ttitle = {Importance of {Modeling} in {Hypersonic} {Flight} {Conditions}},\n\tauthor = {Hanquist, Kyle M.},\n\tyear = {2021},\n\tkeywords = {invited, own},\n}\n\n\n\n
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\n \n\n \n \n Sawicki, P.; Chaudhry, R. S.; and Boyd, I. D.\n\n\n \n \n \n \n \n Influence of chemical kinetics models on plasma generation in hypersonic flight.\n \n \n \n \n\n\n \n\n\n\n In pages 1–16, 2021. American Institute of Aeronautics and Astronautics Inc, AIAA\n \n\n\n\n
\n\n\n\n \n \n \"InfluencePaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{sawicki2021,\n\ttitle = {Influence of chemical kinetics models on plasma generation in hypersonic flight},\n\turl = {https://arc.aiaa.org/doi/abs/10.2514/6.2021-0057},\n\tdoi = {10.2514/6.2021-0057},\n\tabstract = {The accuracy and sensitivity of plasma generation predicted by several different chemical kinetics models is investigated in the context of weakly ionized hypersonic flowfields around the RAM-C (Ra-dio Attenuation Measurement) vehicle. A computational fluid dynamics analysis is used to examine thirteen independent trajectory points along the RAM-C II flight and an assessment of the chemistry models is made by comparing results to available flight measurements. The limitations of making such comparisons with the flight data are established in detail. Two separate geometries are evaluated in this study, as the initial RAM-C geometry was altered during flight after its nose-cap was pyrotechnically ejected. The blunter post-ejection geometry generates more electrons in the stagnation region. In general, good agreement is found between each chemistry model and flight data from both the electrostatic probe and reflectometer stations above 56 km. An expected sizable gap exists between the simulations and reflectometer data at lower altitudes. The impact of forward reaction rates, equilibrium constants, and number of species varies considerably based on altitude, velocity, and position along the body. The commonly analyzed 61 km trajectory point provides a more direct comparison of the various chemistry models, but due care must be given to account for the interpola-tive nature of the reflectometer measurements.},\n\tpublisher = {American Institute of Aeronautics and Astronautics Inc, AIAA},\n\tauthor = {Sawicki, Pawel and Chaudhry, Ross S. and Boyd, Iain D.},\n\tyear = {2021},\n\tpages = {1--16},\n}\n\n\n\n
\n
\n\n\n
\n The accuracy and sensitivity of plasma generation predicted by several different chemical kinetics models is investigated in the context of weakly ionized hypersonic flowfields around the RAM-C (Ra-dio Attenuation Measurement) vehicle. A computational fluid dynamics analysis is used to examine thirteen independent trajectory points along the RAM-C II flight and an assessment of the chemistry models is made by comparing results to available flight measurements. The limitations of making such comparisons with the flight data are established in detail. Two separate geometries are evaluated in this study, as the initial RAM-C geometry was altered during flight after its nose-cap was pyrotechnically ejected. The blunter post-ejection geometry generates more electrons in the stagnation region. In general, good agreement is found between each chemistry model and flight data from both the electrostatic probe and reflectometer stations above 56 km. An expected sizable gap exists between the simulations and reflectometer data at lower altitudes. The impact of forward reaction rates, equilibrium constants, and number of species varies considerably based on altitude, velocity, and position along the body. The commonly analyzed 61 km trajectory point provides a more direct comparison of the various chemistry models, but due care must be given to account for the interpola-tive nature of the reflectometer measurements.\n
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\n \n\n \n \n Ortega, S. T\n\n\n \n \n \n \n Inequitable Access to Graduate School Is Holding Back the Economy.\n \n \n \n\n\n \n\n\n\n Barron's. 2021.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{ortega2021,\n\ttitle = {Inequitable {Access} to {Graduate} {School} {Is} {Holding} {Back} the {Economy}},\n\tjournal = {Barron's},\n\tauthor = {Ortega, Suzanne T},\n\tyear = {2021},\n}\n\n\n\n
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\n \n\n \n \n Torres, E.; Bellas-Chatzigeorgis, G.; and Magin, T. E.\n\n\n \n \n \n \n How to build coarse-grain transport models consistent from the kinetic to fluid regimes.\n \n \n \n\n\n \n\n\n\n Physics of Fluids, 33(3). March 2021.\n Publisher: AIP Publishing LLC AIP Publishing\n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{torres2021,\n\ttitle = {How to build coarse-grain transport models consistent from the kinetic to fluid regimes},\n\tvolume = {33},\n\tdoi = {10.1063/5.0037133},\n\tabstract = {In this paper, we examine how to build coarse-grain transport models consistently from the kinetic to fluid regimes. The internal energy of the gas particles is described through a state-to-state a...},\n\tnumber = {3},\n\tjournal = {Physics of Fluids},\n\tauthor = {Torres, Erik and Bellas-Chatzigeorgis, Georgios and Magin, Thierry E.},\n\tmonth = mar,\n\tyear = {2021},\n\tnote = {Publisher: AIP Publishing LLC AIP Publishing},\n}\n\n\n\n
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\n In this paper, we examine how to build coarse-grain transport models consistently from the kinetic to fluid regimes. The internal energy of the gas particles is described through a state-to-state a...\n
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\n \n\n \n \n Bhattrai, S.; McQuellin, L. P.; Currao, G. M. D.; Neely, A. J.; and Buttsworth, D. R.\n\n\n \n \n \n \n \n Experimental Study of Aeroelastic Response and Performance of a Hypersonic Intake Ramp.\n \n \n \n \n\n\n \n\n\n\n Journal of Propulsion and Power,1–14. September 2021.\n Publisher: American Institute of Aeronautics and Astronautics\n\n\n\n
\n\n\n\n \n \n \"ExperimentalPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{bhattrai2021,\n\ttitle = {Experimental {Study} of {Aeroelastic} {Response} and {Performance} of a {Hypersonic} {Intake} {Ramp}},\n\turl = {https://arc.aiaa.org/doi/abs/10.2514/1.B38348},\n\tdoi = {10.2514/1.B38348},\n\tabstract = {The response and performance of an aeroelastic hypersonic intake was studied experimentally using fundamental geometry and structural boundary conditions. The experiments were conducted in a hypers...},\n\tjournal = {Journal of Propulsion and Power},\n\tauthor = {Bhattrai, Sudip and McQuellin, Liam P. and Currao, Gaetano M. D. and Neely, Andrew J. and Buttsworth, David R.},\n\tmonth = sep,\n\tyear = {2021},\n\tnote = {Publisher: American Institute of Aeronautics and Astronautics},\n\tkeywords = {Aeroelastic Response, Boundary Layer Separation, Cantilever Beam, Hysteresis, Mach Cones, Pitot Probes, Pressure Sensitive Paint, Pressure Transducers, Reynolds Averaged Navier Stokes, Structural Response},\n\tpages = {1--14},\n}\n\n\n\n
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\n The response and performance of an aeroelastic hypersonic intake was studied experimentally using fundamental geometry and structural boundary conditions. The experiments were conducted in a hypers...\n
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\n \n\n \n \n Venegas, C. V.; and Huang, D.\n\n\n \n \n \n \n Expedient Hypersonic Aerothermal Prediction for Aerothermoelastic Analysis Via Field Inversion and Machine Learning.\n \n \n \n\n\n \n\n\n\n In 2021. AIAA Paper 2021-1707\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{venegas2021,\n\ttitle = {Expedient {Hypersonic} {Aerothermal} {Prediction} for {Aerothermoelastic} {Analysis} {Via} {Field} {Inversion} and {Machine} {Learning}},\n\tdoi = {10.2514/6.2021-1707},\n\tabstract = {The accurate and efficient prediction of aerothermal loads over the hypersonic vehicles during atmospheric flight is critical for the aerothermoelastic design, analysis and optimization of the structures of this class of vehicles. Reduced-order models (ROMs) and surrogates are typical approaches to reducing the computational cost to a tractable level. However, the existing ROMs and surrogates suffer from the curse of dimensionality that roots from the need to parameterize and sample the thermal-structural responses. This work presents a novel physics-informed ROM for the aerothermal load calculation on a deforming structure in high-speed flow, based on the combination of the classical turbulent viscous-inviscid interaction (TVI) model and the field inversion and machine learning technique. It is demonstrated that the new model, termed augmented TVI model, can achieve an accuracy close to that of CFD solvers when predicting the flow solutions over a wide range of complex surface deformations with a limited number of high-fidelity solutions. These results underline its potential to be used as a new generation of ROM for the aerothermal load prediction in hypersonic aerothermoelastic design and analysis.},\n\tpublisher = {AIAA Paper 2021-1707},\n\tauthor = {Venegas, Carlos Vargas and Huang, Daning},\n\tyear = {2021},\n}\n\n\n\n
\n
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\n The accurate and efficient prediction of aerothermal loads over the hypersonic vehicles during atmospheric flight is critical for the aerothermoelastic design, analysis and optimization of the structures of this class of vehicles. Reduced-order models (ROMs) and surrogates are typical approaches to reducing the computational cost to a tractable level. However, the existing ROMs and surrogates suffer from the curse of dimensionality that roots from the need to parameterize and sample the thermal-structural responses. This work presents a novel physics-informed ROM for the aerothermal load calculation on a deforming structure in high-speed flow, based on the combination of the classical turbulent viscous-inviscid interaction (TVI) model and the field inversion and machine learning technique. It is demonstrated that the new model, termed augmented TVI model, can achieve an accuracy close to that of CFD solvers when predicting the flow solutions over a wide range of complex surface deformations with a limited number of high-fidelity solutions. These results underline its potential to be used as a new generation of ROM for the aerothermal load prediction in hypersonic aerothermoelastic design and analysis.\n
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\n \n\n \n \n Campbell, N. S.; Hanquist, K. M.; Morin, A.; Meyers, J.; and Boyd, I.\n\n\n \n \n \n \n Evaluation of Computational Models for Electron Transpiration Cooling.\n \n \n \n\n\n \n\n\n\n Aerospace, 8(9). 2021.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{campbell2021,\n\ttitle = {Evaluation of {Computational} {Models} for {Electron} {Transpiration} {Cooling}},\n\tvolume = {8},\n\tdoi = {10.3390/AEROSPACE8090243},\n\tabstract = {Recent developments in the world of hypersonic flight have brought increased attention to the thermal response of materials exposed to high-enthalpy gases. One promising concept is electron transpiration cooling (ETC) that provides the prospect of a passive heat removal mechanism, rivaling and possibly outperforming that of radiative cooling. In this work, non-equilibrium CFD simulations are performed to evaluate the possible roles of this cooling mode under high-enthalpy conditions obtainable in plasma torch ground-test facilities capable of long flow times. The work focuses on the test case of argon gas being heated to achieve enthalpies equivalent to post-shock conditions experienced by a vehicle flying through the atmosphere at hypersonic speed. Simulations are performed at a range of conditions and are used to calibrate direct comparisons between torch operating conditions and resulting flow properties. These comparisons highlight important modeling considerations for simulating long-duration, hot chamber tests. Simulation results correspond well with the experimental measurements of gas temperature, material surface temperature as well as measured current generated in the test article. Theoretical methods taking into consideration space charge limitations are presented and applied to provide design suggestions to boost the ETC effect in future experiments.},\n\tnumber = {9},\n\tjournal = {Aerospace},\n\tauthor = {Campbell, Nicholas S. and Hanquist, Kyle M. and Morin, Andrew and Meyers, Jason and Boyd, Iain},\n\tyear = {2021},\n\tkeywords = {equilibrium gas dynamics, gas, hypersonic flight, non, own, plasma and ionized flows, surface interaction},\n}\n\n\n\n
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\n Recent developments in the world of hypersonic flight have brought increased attention to the thermal response of materials exposed to high-enthalpy gases. One promising concept is electron transpiration cooling (ETC) that provides the prospect of a passive heat removal mechanism, rivaling and possibly outperforming that of radiative cooling. In this work, non-equilibrium CFD simulations are performed to evaluate the possible roles of this cooling mode under high-enthalpy conditions obtainable in plasma torch ground-test facilities capable of long flow times. The work focuses on the test case of argon gas being heated to achieve enthalpies equivalent to post-shock conditions experienced by a vehicle flying through the atmosphere at hypersonic speed. Simulations are performed at a range of conditions and are used to calibrate direct comparisons between torch operating conditions and resulting flow properties. These comparisons highlight important modeling considerations for simulating long-duration, hot chamber tests. Simulation results correspond well with the experimental measurements of gas temperature, material surface temperature as well as measured current generated in the test article. Theoretical methods taking into consideration space charge limitations are presented and applied to provide design suggestions to boost the ETC effect in future experiments.\n
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\n \n\n \n \n Parent, B.\n\n\n \n \n \n \n Electron heating and cooling in hypersonic flows.\n \n \n \n\n\n \n\n\n\n Physics of Fluids, 33(4): 046105–046105. April 2021.\n Publisher: AIP Publishing LLC AIP Publishing\n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{parent2021c,\n\ttitle = {Electron heating and cooling in hypersonic flows},\n\tvolume = {33},\n\tdoi = {10.1063/5.0046197},\n\tabstract = {Using recently developed advanced numerical methods for plasma flows and sheaths, the first detailed study of electron cooling and heating taking place within hypersonic non-neutral flows is presen...},\n\tnumber = {4},\n\tjournal = {Physics of Fluids},\n\tauthor = {Parent, B.},\n\tmonth = apr,\n\tyear = {2021},\n\tnote = {Publisher: AIP Publishing LLC AIP Publishing},\n\tpages = {046105--046105},\n}\n\n\n\n
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\n Using recently developed advanced numerical methods for plasma flows and sheaths, the first detailed study of electron cooling and heating taking place within hypersonic non-neutral flows is presen...\n
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\n \n\n \n \n Parent, B.; Hanquist, K. M.; Rajendran, P. T.; and Liza, M. E.\n\n\n \n \n \n \n Effect of cesium seeding on plasma density in hypersonic boundary layers.\n \n \n \n\n\n \n\n\n\n In AIAA SCITECH 2021 Forum, 2021. AIAA Paper 2021-1251\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n\n\n\n
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@inproceedings{parent2021b,\n\ttitle = {Effect of cesium seeding on plasma density in hypersonic boundary layers},\n\tdoi = {10.2514/6.2021-1251},\n\tabstract = {© 2021, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved. This paper outlines the effect of cesium seeding on the plasma density within the boundary layer around a wedge with a sharp leading edge in the Mach number range 6–18. The results are obtained through numerical simulation using two CFD codes, LeMANS and CFDWARP, which include finite-rate chemistry, non-equilibrium of the vibrational and electron energies, and real gas effects. Results obtained indicate that seeding the air flow with as little as 0.001\\% of cesium leads to plasma densities high enough to interfere with radio communication and to enable electron transpiration cooling (ETC) at flight Mach numbers as little as 9. When no cesium is added, it is seen that significant interference of the plasma on radio communication can occur in the Mach number range 12–18, with the interference becoming more likely for higher flight dynamic pressure.},\n\tbooktitle = {{AIAA} {SCITECH} 2021 {Forum}},\n\tpublisher = {AIAA Paper 2021-1251},\n\tauthor = {Parent, Bernard and Hanquist, Kyle M. and Rajendran, Prasanna T. and Liza, Martin E.},\n\tyear = {2021},\n\tkeywords = {own},\n}\n\n\n\n
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\n © 2021, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved. This paper outlines the effect of cesium seeding on the plasma density within the boundary layer around a wedge with a sharp leading edge in the Mach number range 6–18. The results are obtained through numerical simulation using two CFD codes, LeMANS and CFDWARP, which include finite-rate chemistry, non-equilibrium of the vibrational and electron energies, and real gas effects. Results obtained indicate that seeding the air flow with as little as 0.001% of cesium leads to plasma densities high enough to interfere with radio communication and to enable electron transpiration cooling (ETC) at flight Mach numbers as little as 9. When no cesium is added, it is seen that significant interference of the plasma on radio communication can occur in the Mach number range 12–18, with the interference becoming more likely for higher flight dynamic pressure.\n
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\n \n\n \n \n Gallis, M. A.; and Torczynski, J. R.\n\n\n \n \n \n \n \n Effect of slip on vortex shedding from a circular cylinder in a gas flow.\n \n \n \n \n\n\n \n\n\n\n Physical Review Fluids, 6(6): 063402–063402. June 2021.\n Publisher: American Physical Society\n\n\n\n
\n\n\n\n \n \n \"EffectPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{gallis2021,\n\ttitle = {Effect of slip on vortex shedding from a circular cylinder in a gas flow},\n\tvolume = {6},\n\turl = {https://journals.aps.org/prfluids/abstract/10.1103/PhysRevFluids.6.063402},\n\tdoi = {10.1103/PHYSREVFLUIDS.6.063402},\n\tabstract = {Most studies of vortex shedding from a circular cylinder in a gas flow have explicitly or implicitly assumed that the no-slip condition applies on the cylinder surface. To investigate the effect of slip, vortex shedding is simulated using molecular gas dynamics (the direct simulation Monte Carlo method) and computational fluid dynamics (the incompressible Navier-Stokes equations with a slip boundary condition). A Reynolds number of 100, a Mach number of 0.3, and a corresponding Knudsen number of 0.0048 are examined. For these conditions, compressibility effects are small, and periodic laminar vortex shedding is obtained. Slip on the cylinder is varied using combinations of diffuse and specular molecular reflections with accommodation coefficients from zero (maximum slip) to unity (minimum slip). Although unrealistic, bounce-back molecular reflections are also examined because they approximate the no-slip boundary condition (zero slip). The results from both methods are in reasonable agreement. The shedding frequency increases slightly as the accommodation coefficient is decreased, and shedding ceases at low accommodation coefficients (large slip). The streamwise and transverse forces decrease as the accommodation coefficient is decreased. Based on the good agreement between the two methods, computational fluid dynamics is used to determine the critical accommodation coefficient below which vortex shedding ceases for Reynolds numbers of 60-100 at a Mach number of 0.3. Conditions to observe the effect of slip on vortex shedding appear to be experimentally realizable, although challenging.},\n\tnumber = {6},\n\tjournal = {Physical Review Fluids},\n\tauthor = {Gallis, M. A. and Torczynski, J. R.},\n\tmonth = jun,\n\tyear = {2021},\n\tnote = {Publisher: American Physical Society},\n\tpages = {063402--063402},\n}\n\n\n\n
\n
\n\n\n
\n Most studies of vortex shedding from a circular cylinder in a gas flow have explicitly or implicitly assumed that the no-slip condition applies on the cylinder surface. To investigate the effect of slip, vortex shedding is simulated using molecular gas dynamics (the direct simulation Monte Carlo method) and computational fluid dynamics (the incompressible Navier-Stokes equations with a slip boundary condition). A Reynolds number of 100, a Mach number of 0.3, and a corresponding Knudsen number of 0.0048 are examined. For these conditions, compressibility effects are small, and periodic laminar vortex shedding is obtained. Slip on the cylinder is varied using combinations of diffuse and specular molecular reflections with accommodation coefficients from zero (maximum slip) to unity (minimum slip). Although unrealistic, bounce-back molecular reflections are also examined because they approximate the no-slip boundary condition (zero slip). The results from both methods are in reasonable agreement. The shedding frequency increases slightly as the accommodation coefficient is decreased, and shedding ceases at low accommodation coefficients (large slip). The streamwise and transverse forces decrease as the accommodation coefficient is decreased. Based on the good agreement between the two methods, computational fluid dynamics is used to determine the critical accommodation coefficient below which vortex shedding ceases for Reynolds numbers of 60-100 at a Mach number of 0.3. Conditions to observe the effect of slip on vortex shedding appear to be experimentally realizable, although challenging.\n
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\n \n\n \n \n Chengalrayan, S.; Pascual, R.; Shkarayev, S. V.; and Hanquist, K. M.\n\n\n \n \n \n \n Determination of Flow Field and Structural Parameters using Inverse Interpolation Methods.\n \n \n \n\n\n \n\n\n\n 2021.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n\n\n\n
\n 
@misc{chengalrayan2021,\n\taddress = {74th Annual Meeting of the Division of Fluid Dynamics, American Physical Society},\n\ttype = {Conference {Presentation}},\n\ttitle = {Determination of {Flow} {Field} and {Structural} {Parameters} using {Inverse} {Interpolation} {Methods}},\n\tauthor = {Chengalrayan, Sruthi and Pascual, Rodrigo and Shkarayev, Sergey V. and Hanquist, Kyle M.},\n\tyear = {2021},\n\tkeywords = {own, presentation},\n}\n\n\n\n
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\n  \n 2020\n \n \n (52)\n \n \n
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\n \n\n \n \n Venturi, S.; Sharma, M. P.; Lopez, B.; and Panesi, M.\n\n\n \n \n \n \n \n Data-Inspired and Physics-Driven Model Reduction for Dissociation: Application to the O$_{\\textrm{2}}$+O System.\n \n \n \n \n\n\n \n\n\n\n Journal of Physical Chemistry A, 124(41): 8359–8372. October 2020.\n Publisher: American Chemical Society\n\n\n\n
\n\n\n\n \n \n \"Data-InspiredPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{venturi2020a,\n\ttitle = {Data-{Inspired} and {Physics}-{Driven} {Model} {Reduction} for {Dissociation}: {Application} to the {O}$_{\\textrm{2}}$+{O} {System}},\n\tvolume = {124},\n\turl = {https://pubs.acs.org/doi/full/10.1021/acs.jpca.0c04516},\n\tdoi = {10.1021/ACS.JPCA.0C04516/ASSET/IMAGES/MEDIUM/JP0C04516_M040.GIF},\n\tabstract = {This work presents an in-depth discussion on the nonequilibrium dissociation of O2 molecules colliding with O atoms, combining quasi-classical trajectory calculations, master equation, and dimensionality reduction. A rovibrationally resolved database for all of the elementary collisional processes is constructed by including all nine adiabatic electronic states of O3 in the QCT calculations. A detailed analysis of the ab initio data set reveals that for a rovibrational level, the probability of dissociating is mostly dictated by its deficit in internal energy compared to the centrifugal barrier. Because of the assumption of rotational equilibrium, the conventional vibrational-specific calculations fail to characterize such a dependence. Based on this observation, a new physics-based grouping strategy for application to coarse-grained models is proposed. By relying on a hybrid technique made of rovibrationally resolved excitation coupled to coarse-grained dissociation, the new approach is compared to the vibrational-specific model and the direct solution of the rovibrational state-to-state master equation. Simulations are performed in a zero-dimensional isothermal and isochoric chemical reactor for a wide range of temperatures (1500-20,000 K). The study shows that the main contribution to the model inadequacy of vibrational-specific approaches originates from the incapability of characterizing dissociation, rather than the energy transfers. Even when constructed with only twenty groups, the new reduced-order model outperforms the vibrational-specific one in predicting all of the QoIs related to dissociation kinetics. At the highest temperature, the accuracy in the mole fraction is improved by 2000\\%.},\n\tnumber = {41},\n\tjournal = {Journal of Physical Chemistry A},\n\tauthor = {Venturi, S. and Sharma, M. P. and Lopez, B. and Panesi, M.},\n\tmonth = oct,\n\tyear = {2020},\n\tnote = {Publisher: American Chemical Society},\n\tpages = {8359--8372},\n}\n\n\n\n
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\n This work presents an in-depth discussion on the nonequilibrium dissociation of O2 molecules colliding with O atoms, combining quasi-classical trajectory calculations, master equation, and dimensionality reduction. A rovibrationally resolved database for all of the elementary collisional processes is constructed by including all nine adiabatic electronic states of O3 in the QCT calculations. A detailed analysis of the ab initio data set reveals that for a rovibrational level, the probability of dissociating is mostly dictated by its deficit in internal energy compared to the centrifugal barrier. Because of the assumption of rotational equilibrium, the conventional vibrational-specific calculations fail to characterize such a dependence. Based on this observation, a new physics-based grouping strategy for application to coarse-grained models is proposed. By relying on a hybrid technique made of rovibrationally resolved excitation coupled to coarse-grained dissociation, the new approach is compared to the vibrational-specific model and the direct solution of the rovibrational state-to-state master equation. Simulations are performed in a zero-dimensional isothermal and isochoric chemical reactor for a wide range of temperatures (1500-20,000 K). The study shows that the main contribution to the model inadequacy of vibrational-specific approaches originates from the incapability of characterizing dissociation, rather than the energy transfers. Even when constructed with only twenty groups, the new reduced-order model outperforms the vibrational-specific one in predicting all of the QoIs related to dissociation kinetics. At the highest temperature, the accuracy in the mole fraction is improved by 2000%.\n
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\n \n\n \n \n Wignall, T; and Houlden, H.\n\n\n \n \n \n \n Uncertainty Quantification for Launch Vehicle Aerodynamic Lineloads.\n \n \n \n\n\n \n\n\n\n In AIAA Scitech Forum, January 2020. \n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{wignall2020,\n\ttitle = {Uncertainty {Quantification} for {Launch} {Vehicle} {Aerodynamic} {Lineloads}},\n\tdoi = {10.2514/6.2020-1521},\n\tbooktitle = {{AIAA} {Scitech} {Forum}},\n\tauthor = {Wignall, T and Houlden, Heather},\n\tmonth = jan,\n\tyear = {2020},\n}\n\n\n\n
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\n \n\n \n \n Urzay, J; and Renzo, M D.\n\n\n \n \n \n \n \n Engineering aspects of hypersonic turbulent flows at suborbital enthalpies.\n \n \n \n \n\n\n \n\n\n\n Technical Report Center for Turbulence Research, Annual Research Briefs, Stanford University, 2020.\n \n\n\n\n
\n\n\n\n \n \n \"EngineeringPaper\n  \n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@techreport{urzay2020,\n\ttitle = {Engineering aspects of hypersonic turbulent flows at suborbital enthalpies},\n\turl = {https://web.stanford.edu/~jurzay/hypersonicsCh2_Urzay.pdf},\n\tlanguage = {en},\n\tnumber = {Center for Turbulence Research, Annual Research Briefs},\n\tinstitution = {Stanford University},\n\tauthor = {Urzay, J and Renzo, M Di},\n\tyear = {2020},\n}\n\n\n\n
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\n \n\n \n \n Tropina, A.; Andrienko, D. A; and Miles, R. B\n\n\n \n \n \n \n Modeling studies of electron transpiration cooling at high-speed flows.\n \n \n \n\n\n \n\n\n\n In 2020. AIAA Paper 2020-3231\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n\n\n\n
\n 
@inproceedings{tropina2020,\n\ttitle = {Modeling studies of electron transpiration cooling at high-speed flows},\n\tdoi = {10.2514/6.2020-3231},\n\tpublisher = {AIAA Paper 2020-3231},\n\tauthor = {Tropina, Albina and Andrienko, Daniil A and Miles, Richard B},\n\tyear = {2020},\n\tkeywords = {etc},\n}\n\n\n\n\n\n\n\n
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\n \n\n \n \n Bailey, M.\n\n\n \n \n \n \n Frequent and Reliable Launch for Small Satellites: Rocket Lab's Electron Launch Vehicle and Photon Spacecraft.\n \n \n \n\n\n \n\n\n\n Handbook of Small Satellites,453–468. September 2020.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{bailey2020,\n\ttitle = {Frequent and {Reliable} {Launch} for {Small} {Satellites}: {Rocket} {Lab}'s {Electron} {Launch} {Vehicle} and {Photon} {Spacecraft}},\n\tdoi = {https://doi.org/10.1007/978-3-030-36308-6_91#DOI},\n\tjournal = {Handbook of Small Satellites},\n\tauthor = {Bailey, Morgan},\n\tmonth = sep,\n\tyear = {2020},\n\tpages = {453--468},\n}\n\n\n\n
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\n \n\n \n \n Yao, Y.; Xue, W.; Wang, T.; Wu, Y.; and Xu, L.\n\n\n \n \n \n \n \n Influence of LOS angle on aero-optics imaging deviation.\n \n \n \n \n\n\n \n\n\n\n Optik, 202: 163732. February 2020.\n \n\n\n\n
\n\n\n\n \n \n \"InfluencePaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{Yao2020,\n\ttitle = {Influence of {LOS} angle on aero-optics imaging deviation},\n\tvolume = {202},\n\tissn = {00304026},\n\turl = {https://linkinghub.elsevier.com/retrieve/pii/S0030402619316304},\n\tdoi = {10.1016/j.ijleo.2019.163732},\n\tjournal = {Optik},\n\tauthor = {Yao, Yuan and Xue, Wei and Wang, Tao and Wu, Yuyang and Xu, Liang},\n\tmonth = feb,\n\tyear = {2020},\n\tpages = {163732},\n}\n\n\n\n
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\n \n\n \n \n Sadagopan, A.; Huang, D.; and Hanquist, K.\n\n\n \n \n \n \n Impact of high-temperature effects on the aerothermoelastic behavior of composite skin panels in hypersonic flow.\n \n \n \n\n\n \n\n\n\n In AIAA SCITEH 2020 Forum, 2020. AIAA Paper 2020-0937\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n\n\n\n
\n 
@inproceedings{sadagopan2020,\n\ttitle = {Impact of high-temperature effects on the aerothermoelastic behavior of composite skin panels in hypersonic flow},\n\tdoi = {10.2514/6.2020-0937},\n\tabstract = {© 2020, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved. This study investigates the impact of the high-temperature effect, esp. the real gas effect and the chemical reactions, on hypersonic aerothermodynamic solutions and the aerothermoelastic behavior of a typical skin panel in hypersonic flow. First, several computational fluid dynamics codes that were developed in significantly different ways were benchmarked and compared for hypersonic aerothermodynamics, emphasizing the impact of high-temperature effects as well as turbulence modeling on heat flux prediction. Subsequently, a reduced-order model (ROM) for hypersonic aerothermal loads accounting for the high-temperature effect is developed. Particularly, a ROM correction approach for high-temperature effect was presented, so that a ROM constructed based on the perfect gas assumption can generate fluid solutions that account for the real gas effect with reasonable accuracy. Finally, the new fluid ROM was applied to study the impact of the high-temperature effect on the aerothermoelastic response of a hypersonic skin panel, with an emphasis on its stability boundary.},\n\tbooktitle = {{AIAA} {SCITEH} 2020 {Forum}},\n\tpublisher = {AIAA Paper 2020-0937},\n\tauthor = {Sadagopan, A. and Huang, D. and Hanquist, K.},\n\tyear = {2020},\n\tkeywords = {own},\n}\n\n\n\n
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\n © 2020, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved. This study investigates the impact of the high-temperature effect, esp. the real gas effect and the chemical reactions, on hypersonic aerothermodynamic solutions and the aerothermoelastic behavior of a typical skin panel in hypersonic flow. First, several computational fluid dynamics codes that were developed in significantly different ways were benchmarked and compared for hypersonic aerothermodynamics, emphasizing the impact of high-temperature effects as well as turbulence modeling on heat flux prediction. Subsequently, a reduced-order model (ROM) for hypersonic aerothermal loads accounting for the high-temperature effect is developed. Particularly, a ROM correction approach for high-temperature effect was presented, so that a ROM constructed based on the perfect gas assumption can generate fluid solutions that account for the real gas effect with reasonable accuracy. Finally, the new fluid ROM was applied to study the impact of the high-temperature effect on the aerothermoelastic response of a hypersonic skin panel, with an emphasis on its stability boundary.\n
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\n \n\n \n \n MacDonald, M. E.; Philippidis, D.; Haw, M.; Schickele, D.; Luis, D.; Hartman, J.; and McGlaughlin, M.\n\n\n \n \n \n \n \n Initial Characterization of the 30 kW Miniature Arc Jet (mARC II) at NASA Ames Research Center.\n \n \n \n \n\n\n \n\n\n\n In AIAA AVIATION 2020 FORUM, 2020. AIAA Paper 2020-3108\n \n\n\n\n
\n\n\n\n \n \n \"InitialPaper\n  \n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{macdonald2020a,\n\ttitle = {Initial {Characterization} of the 30 {kW} {Miniature} {Arc} {Jet} ({mARC} {II}) at {NASA} {Ames} {Research} {Center}},\n\turl = {https://arc.aiaa.org/doi/abs/10.2514/6.2020-3108},\n\tabstract = {The second-generation Miniature Arc jet Research Chamber (mARC II) at NASA Ames is undergoing integrated systems testing. Once fully operational, this facility will be added to the range of available test facilities operated by the NASA Ames Thermophysics Facilities Branch, with primary focus on applications such as new arc jet flow diagnostics and new arc column diagnostics. Initial characterization of the mARC II is reported here, specifically, measured arc current, arc voltage, column and chamber pressures, mass flow rates, and initial emission measurements carried out at a range of conditions.},\n\turldate = {2024-04-26},\n\tbooktitle = {{AIAA} {AVIATION} 2020 {FORUM}},\n\tpublisher = {AIAA Paper 2020-3108},\n\tauthor = {MacDonald, Megan E. and Philippidis, Daniel and Haw, Magnus and Schickele, Daniel and Luis, Diana and Hartman, Joe and McGlaughlin, Mark},\n\tyear = {2020},\n}\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n
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\n The second-generation Miniature Arc jet Research Chamber (mARC II) at NASA Ames is undergoing integrated systems testing. Once fully operational, this facility will be added to the range of available test facilities operated by the NASA Ames Thermophysics Facilities Branch, with primary focus on applications such as new arc jet flow diagnostics and new arc column diagnostics. Initial characterization of the mARC II is reported here, specifically, measured arc current, arc voltage, column and chamber pressures, mass flow rates, and initial emission measurements carried out at a range of conditions.\n
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\n \n\n \n \n Leake, C.; and Mortari, D.\n\n\n \n \n \n \n Deep Theory of Functional Connections: A New Method for Estimating the Solutions of Partial Differential Equations.\n \n \n \n\n\n \n\n\n\n Machine Learning and Knowledge Extraction, 2(1): 37–55. March 2020.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{leake2020,\n\ttitle = {Deep {Theory} of {Functional} {Connections}: {A} {New} {Method} for {Estimating} the {Solutions} of {Partial} {Differential} {Equations}},\n\tvolume = {2},\n\tcopyright = {http://creativecommons.org/licenses/by/3.0/},\n\tissn = {2504-4990},\n\tshorttitle = {Deep {Theory} of {Functional} {Connections}},\n\tdoi = {10.3390/make2010004},\n\tabstract = {This article presents a new methodology called Deep Theory of Functional Connections (TFC) that estimates the solutions of partial differential equations (PDEs) by combining neural networks with the TFC. The TFC is used to transform PDEs into unconstrained optimization problems by analytically embedding the PDE’s constraints into a “constrained expression” containing a free function. In this research, the free function is chosen to be a neural network, which is used to solve the now unconstrained optimization problem. This optimization problem consists of minimizing a loss function that is chosen to be the square of the residuals of the PDE. The neural network is trained in an unsupervised manner to minimize this loss function. This methodology has two major differences when compared with popular methods used to estimate the solutions of PDEs. First, this methodology does not need to discretize the domain into a grid, rather, this methodology can randomly sample points from the domain during the training phase. Second, after training, this methodology produces an accurate analytical approximation of the solution throughout the entire training domain. Because the methodology produces an analytical solution, it is straightforward to obtain the solution at any point within the domain and to perform further manipulation if needed, such as differentiation. In contrast, other popular methods require extra numerical techniques if the estimated solution is desired at points that do not lie on the discretized grid, or if further manipulation to the estimated solution must be performed.},\n\tlanguage = {en},\n\tnumber = {1},\n\turldate = {2024-04-24},\n\tjournal = {Machine Learning and Knowledge Extraction},\n\tauthor = {Leake, Carl and Mortari, Daniele},\n\tmonth = mar,\n\tyear = {2020},\n\tkeywords = {deep learning, neural network, partial differential equation, theory of functional connections},\n\tpages = {37--55},\n}\n\n\n\n
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\n This article presents a new methodology called Deep Theory of Functional Connections (TFC) that estimates the solutions of partial differential equations (PDEs) by combining neural networks with the TFC. The TFC is used to transform PDEs into unconstrained optimization problems by analytically embedding the PDE’s constraints into a “constrained expression” containing a free function. In this research, the free function is chosen to be a neural network, which is used to solve the now unconstrained optimization problem. This optimization problem consists of minimizing a loss function that is chosen to be the square of the residuals of the PDE. The neural network is trained in an unsupervised manner to minimize this loss function. This methodology has two major differences when compared with popular methods used to estimate the solutions of PDEs. First, this methodology does not need to discretize the domain into a grid, rather, this methodology can randomly sample points from the domain during the training phase. Second, after training, this methodology produces an accurate analytical approximation of the solution throughout the entire training domain. Because the methodology produces an analytical solution, it is straightforward to obtain the solution at any point within the domain and to perform further manipulation if needed, such as differentiation. In contrast, other popular methods require extra numerical techniques if the estimated solution is desired at points that do not lie on the discretized grid, or if further manipulation to the estimated solution must be performed.\n
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\n \n\n \n \n Baalrud, S. D.; Scheiner, B.; Yee, B. T.; Hopkins, M. M.; and Barnat, E.\n\n\n \n \n \n \n Interaction of biased electrodes and plasmas: sheaths, double layers, and fireballs.\n \n \n \n\n\n \n\n\n\n Plasma Sources Science and Technology, 29(5): 053001. May 2020.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@article{baalrud2020,\n\ttitle = {Interaction of biased electrodes and plasmas: sheaths, double layers, and fireballs},\n\tvolume = {29},\n\tissn = {0963-0252},\n\tshorttitle = {Interaction of biased electrodes and plasmas},\n\tdoi = {10.1088/1361-6595/ab8177},\n\tabstract = {Biased electrodes are common components of plasma sources and diagnostics. The plasma–electrode interaction is mediated by an intervening sheath structure that influences properties of the electrons and ions contacting the electrode surface, as well as properties of the bulk plasma. A rich variety of sheath structures have been observed, including ion sheaths, electron sheaths, double sheaths, double layers, anode glow, and fireballs. These represent complex self-organized responses of the plasma that depend not only on the local influence of the electrode, but also on the global properties of the plasma and the other boundaries that it is in contact with. This review summarizes recent advances in understanding the conditions under which each type of sheath forms, what the basic stability criteria and steady-state properties of each are, and the ways in which each can influence plasma–boundary interactions and bulk plasma properties. These results may be of interest to a number of application areas where biased electrodes are used, including diagnostics, plasma modification of materials, plasma sources, electric propulsion, and the interaction of plasmas with objects in space.},\n\tlanguage = {en},\n\tnumber = {5},\n\turldate = {2024-04-24},\n\tjournal = {Plasma Sources Science and Technology},\n\tauthor = {Baalrud, Scott D. and Scheiner, Brett and Yee, Benjamin T. and Hopkins, Matthew M. and Barnat, Edward},\n\tmonth = may,\n\tyear = {2020},\n\tpages = {053001},\n}\n\n\n\n
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\n Biased electrodes are common components of plasma sources and diagnostics. The plasma–electrode interaction is mediated by an intervening sheath structure that influences properties of the electrons and ions contacting the electrode surface, as well as properties of the bulk plasma. A rich variety of sheath structures have been observed, including ion sheaths, electron sheaths, double sheaths, double layers, anode glow, and fireballs. These represent complex self-organized responses of the plasma that depend not only on the local influence of the electrode, but also on the global properties of the plasma and the other boundaries that it is in contact with. This review summarizes recent advances in understanding the conditions under which each type of sheath forms, what the basic stability criteria and steady-state properties of each are, and the ways in which each can influence plasma–boundary interactions and bulk plasma properties. These results may be of interest to a number of application areas where biased electrodes are used, including diagnostics, plasma modification of materials, plasma sources, electric propulsion, and the interaction of plasmas with objects in space.\n
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\n \n\n \n \n Adams, B. M.; Bohnhoff, W. J.; Dalbey, K. R.; Ebeida, M. S.; Eddy, J. P.; Eldred, M. S.; Hooper, R. W.; Hough, P. D.; Hu, K. T.; Jakeman, J. D.; Khalil, M.; Maupin, K. A.; Monschke, J. A.; Ridgway, E. M.; Rushdi, A. .; Seidl, D. T.; Stephens, J. A.; and Winokur, J. G.\n\n\n \n \n \n \n Dakota, a multilevel parallel object-oriented framework for design optimization, parameter estimation, uncertainty quantification, and sensitivity analysis: Version 6.13 user's manual.\n \n \n \n\n\n \n\n\n\n . November 2020.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{adams2020,\n\ttitle = {Dakota, a multilevel parallel object-oriented framework for design optimization, parameter estimation, uncertainty quantification, and sensitivity analysis: {Version} 6.13 user's manual},\n\tdoi = {10.2172/1817318},\n\tauthor = {Adams, Brian M. and Bohnhoff, William J. and Dalbey, Keith R. and Ebeida, Mohamed S. and Eddy, John P. and Eldred, Michael S. and Hooper, Russell W. and Hough, Patricia D. and Hu, Kenneth T. and Jakeman, John D. and Khalil, Mohammad and Maupin, Kathryn A. and Monschke, Jason A. and Ridgway, Elliott M. and Rushdi, Ahmad . and Seidl, Daniel Thomas and Stephens, John Adam and Winokur, Justin G.},\n\tmonth = nov,\n\tyear = {2020},\n}\n\n\n\n
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\n \n\n \n \n Blanco, A.; and Josyula, E.\n\n\n \n \n \n \n Numerical Modeling of Hypersonic Weakly Ionized External Flowfields with Poisson’s Equation.\n \n \n \n\n\n \n\n\n\n AIAA Journal, 58(8): 3464–3475. May 2020.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
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@article{blanco2020,\n\ttitle = {Numerical {Modeling} of {Hypersonic} {Weakly} {Ionized} {External} {Flowfields} with {Poisson}’s {Equation}},\n\tvolume = {58},\n\tdoi = {10.2514/1.J059307},\n\tabstract = {A seven-species air model is used to numerically simulate and analyze the flowfield of an air plasma. Previous numerical models have employed different electric field approximations that assume amb...},\n\tnumber = {8},\n\tjournal = {AIAA Journal},\n\tauthor = {Blanco, Ariel and Josyula, Eswar},\n\tmonth = may,\n\tyear = {2020},\n\tkeywords = {Courant Friedrichs Lewy, Freestream Velocity, No Slip Condition, Nonequilibrium Flows, Nonequilibrium Plasmas, Numerical Modeling, Poisson's Equation, Shock Layers, Thermal Flux, Velocity Distribution Function},\n\tpages = {3464--3475},\n}\n\n\n\n
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\n A seven-species air model is used to numerically simulate and analyze the flowfield of an air plasma. Previous numerical models have employed different electric field approximations that assume amb...\n
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\n \n\n \n \n Terrani, K.; Jolly, B.; and Trammell, M.\n\n\n \n \n \n \n 3D printing of high-purity silicon carbide.\n \n \n \n\n\n \n\n\n\n Journal of the American Ceramic Society, 103(3): 1575–1581. 2020.\n _eprint: https://onlinelibrary.wiley.com/doi/pdf/10.1111/jace.16888\n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{terrani_3d_2020,\n\ttitle = {{3D} printing of high-purity silicon carbide},\n\tvolume = {103},\n\tcopyright = {Published 2019. This article is a U.S. Government work and is in the public domain in the USA.},\n\tissn = {1551-2916},\n\tdoi = {10.1111/jace.16888},\n\tabstract = {A method for advanced manufacturing of silicon carbide offering complete freedom in geometric complexity in the three-dimensional space is described. The method combines binder jet printing and chemical vapor infiltration in a process capable of yielding a high-purity, fully crystalline ceramic—attributes essential for ideal performance in very high-temperature applications or in the presence of displacement damage. Thermal conductivity and characteristic equibiaxial flexural strength of the resulting monolithic SiC at room temperature are 37 W·(m·K)−1 and 297 MPa, respectively.},\n\tlanguage = {en},\n\tnumber = {3},\n\turldate = {2023-10-30},\n\tjournal = {Journal of the American Ceramic Society},\n\tauthor = {Terrani, Kurt and Jolly, Brian and Trammell, Michael},\n\tyear = {2020},\n\tnote = {\\_eprint: https://onlinelibrary.wiley.com/doi/pdf/10.1111/jace.16888},\n\tkeywords = {3D printing, processing, silicon carbide},\n\tpages = {1575--1581},\n}\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n
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\n A method for advanced manufacturing of silicon carbide offering complete freedom in geometric complexity in the three-dimensional space is described. The method combines binder jet printing and chemical vapor infiltration in a process capable of yielding a high-purity, fully crystalline ceramic—attributes essential for ideal performance in very high-temperature applications or in the presence of displacement damage. Thermal conductivity and characteristic equibiaxial flexural strength of the resulting monolithic SiC at room temperature are 37 W·(m·K)−1 and 297 MPa, respectively.\n
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\n \n\n \n \n Song, S.; Gao, Z.; Lu, B.; Bao, C.; Zheng, B.; and Wang, L.\n\n\n \n \n \n \n Performance optimization of complicated structural SiC/Si composite ceramics prepared by selective laser sintering.\n \n \n \n\n\n \n\n\n\n Ceramics International, 46(1): 568–575. January 2020.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{song_performance_2020,\n\ttitle = {Performance optimization of complicated structural {SiC}/{Si} composite ceramics prepared by selective laser sintering},\n\tvolume = {46},\n\tissn = {0272-8842},\n\tdoi = {10.1016/j.ceramint.2019.09.004},\n\tabstract = {Combining reaction-bonded (RB) process and selective laser sintering (SLS) method is an effective approach to prepare ceramic components with complex shapes. The purpose of this paper is to find efficient ways to improve the performance of SiC/Si composites prepared by SLS/RB technologies. Effects of epoxy resin binder on the performance and microstructure of preforms and sintered bodies were studied first. Then, based on the above results, graphite with low reactivity was used as an alternative slow-release carbon source to promote sintering densification process and improve the carbon density of preforms. When the added amount of graphite increased, clusters of nanometer-sized SiC grains formed and the silicon phase transformed into pieces, which reduced the content and dimension of silicon phase. Furthermore, by applying a two-step sintering method, the residual silicon content of SiC/Si composites decreased further and the flexural strength at high temperatures increased.},\n\tnumber = {1},\n\turldate = {2023-10-28},\n\tjournal = {Ceramics International},\n\tauthor = {Song, Suocheng and Gao, Zongqiang and Lu, Bingheng and Bao, Chonggao and Zheng, Baochao and Wang, Lei},\n\tmonth = jan,\n\tyear = {2020},\n\tkeywords = {High-temperature behavior, Performance enchantment, Reaction-bonded process, Selective laser sintering},\n\tpages = {568--575},\n}\n\n\n\n\n\n\n\n\n\n\n\n
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\n Combining reaction-bonded (RB) process and selective laser sintering (SLS) method is an effective approach to prepare ceramic components with complex shapes. The purpose of this paper is to find efficient ways to improve the performance of SiC/Si composites prepared by SLS/RB technologies. Effects of epoxy resin binder on the performance and microstructure of preforms and sintered bodies were studied first. Then, based on the above results, graphite with low reactivity was used as an alternative slow-release carbon source to promote sintering densification process and improve the carbon density of preforms. When the added amount of graphite increased, clusters of nanometer-sized SiC grains formed and the silicon phase transformed into pieces, which reduced the content and dimension of silicon phase. Furthermore, by applying a two-step sintering method, the residual silicon content of SiC/Si composites decreased further and the flexural strength at high temperatures increased.\n
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\n \n\n \n \n Xu, T.; Cheng, S.; Jin, L.; Zhang, K.; and Zeng, T.\n\n\n \n \n \n \n High-temperature flexural strength of SiC ceramics prepared by additive manufacturing.\n \n \n \n\n\n \n\n\n\n International Journal of Applied Ceramic Technology, 17(2): 438–448. 2020.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n\n\n\n
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@article{xu_high-temperature_2020,\n\ttitle = {High-temperature flexural strength of {SiC} ceramics prepared by additive manufacturing},\n\tvolume = {17},\n\tcopyright = {© 2019 The American Ceramic Society},\n\tissn = {1744-7402},\n\tdoi = {10.1111/ijac.13454},\n\tabstract = {Silicon carbide (SiC) ceramics, as a kind of candidate material for aero-engine, its high-temperature performance is a critical factor to determine its applicability. This investigation focuses on studying the high-temperature properties of SiC ceramics fabricated by using additive manufacturing technology. In this paper, SiC ceramics were prepared by combining selective laser sintering (SLS) with precursor infiltration and pyrolysis (PIP) technique. The microstructure, phase evolution, and failure mechanism after high-temperature tests were explored. SiC ceramic samples tested at room temperature (RT), 800°C, 1200°C, 1400°C, and 1600°C demonstrated bending strengths of 220.0, 226.1, 234.9, 215.5, and 203.7 MPa, respectively. The RT strength of this material can be maintained at 1400°C, but it decreased at 1600°C. The strength retention at 1400°C and 1600°C were 98\\% and 92\\%, respectively. The results indicate that the mechanical properties of SiC ceramics prepared using this method have excellent stability. As the temperature increases, the bending strength of the specimens increased slightly and reached the peak value at 1200°C, and dropped to 203.7 MPa at 1600°C. Such an evolution could be mainly due to the crack healing, and the softening of the glassy phase.},\n\tlanguage = {en},\n\tnumber = {2},\n\turldate = {2023-10-23},\n\tjournal = {International Journal of Applied Ceramic Technology},\n\tauthor = {Xu, Teng-Teng and Cheng, Su and Jin, Lai-Zhen and Zhang, Kun and Zeng, Tao},\n\tyear = {2020},\n\tkeywords = {high-temperature flexural strength, polymer impregnation process, selective laser sintering, silicon carbide},\n\tpages = {438--448},\n}\n\n\n\n\n\n\n\n
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\n Silicon carbide (SiC) ceramics, as a kind of candidate material for aero-engine, its high-temperature performance is a critical factor to determine its applicability. This investigation focuses on studying the high-temperature properties of SiC ceramics fabricated by using additive manufacturing technology. In this paper, SiC ceramics were prepared by combining selective laser sintering (SLS) with precursor infiltration and pyrolysis (PIP) technique. The microstructure, phase evolution, and failure mechanism after high-temperature tests were explored. SiC ceramic samples tested at room temperature (RT), 800°C, 1200°C, 1400°C, and 1600°C demonstrated bending strengths of 220.0, 226.1, 234.9, 215.5, and 203.7 MPa, respectively. The RT strength of this material can be maintained at 1400°C, but it decreased at 1600°C. The strength retention at 1400°C and 1600°C were 98% and 92%, respectively. The results indicate that the mechanical properties of SiC ceramics prepared using this method have excellent stability. As the temperature increases, the bending strength of the specimens increased slightly and reached the peak value at 1200°C, and dropped to 203.7 MPa at 1600°C. Such an evolution could be mainly due to the crack healing, and the softening of the glassy phase.\n
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\n \n\n \n \n Chen, S. Y.; and Boyd, I. D.\n\n\n \n \n \n \n Boundary-Layer Thermochemical Analysis During Passive and Active Oxidation of Silicon Carbide.\n \n \n \n\n\n \n\n\n\n Journal of Thermophysics and Heat Transfer, 34(3): 504–515. 2020.\n Publisher: American Institute of Aeronautics and Astronautics _eprint: https://doi.org/10.2514/1.T5864\n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{chen_boundary-layer_2020,\n\ttitle = {Boundary-{Layer} {Thermochemical} {Analysis} {During} {Passive} and {Active} {Oxidation} of {Silicon} {Carbide}},\n\tvolume = {34},\n\tissn = {0887-8722},\n\tdoi = {10.2514/1.T5864},\n\tabstract = {Silicon carbide is an ultra-high-temperature ceramic proposed for hypersonic flight applications. However, its use is limited at conditions where oxidation causes aggressive material degradation and a surface temperature “jump” phenomenon. Oxidation is a coupled process, depending on both boundary layer and surface chemistry. An equilibrium surface chemistry model for silicon carbide oxidation is coupled to a nonequilibrium computational fluid dynamics framework, accounting for gas–surface reactions, blowing of oxidation products, and a detailed surface energy balance. Boundary-layer analyses demonstrate a 20–40\\% increase in the chemical diffusive heating during passive-to-active transition, and predicted steady-state temperatures agree with experimental measurements within 3\\%. Simulated emission spectra show good qualitative agreement with spectra measured in high-enthalpy experiments.},\n\tnumber = {3},\n\turldate = {2023-10-09},\n\tjournal = {Journal of Thermophysics and Heat Transfer},\n\tauthor = {Chen, Samuel Y. and Boyd, Iain D.},\n\tyear = {2020},\n\tnote = {Publisher: American Institute of Aeronautics and Astronautics\n\\_eprint: https://doi.org/10.2514/1.T5864},\n\tpages = {504--515},\n}\n\n\n\n\n\n\n\n\n\n\n\n
\n
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\n Silicon carbide is an ultra-high-temperature ceramic proposed for hypersonic flight applications. However, its use is limited at conditions where oxidation causes aggressive material degradation and a surface temperature “jump” phenomenon. Oxidation is a coupled process, depending on both boundary layer and surface chemistry. An equilibrium surface chemistry model for silicon carbide oxidation is coupled to a nonequilibrium computational fluid dynamics framework, accounting for gas–surface reactions, blowing of oxidation products, and a detailed surface energy balance. Boundary-layer analyses demonstrate a 20–40% increase in the chemical diffusive heating during passive-to-active transition, and predicted steady-state temperatures agree with experimental measurements within 3%. Simulated emission spectra show good qualitative agreement with spectra measured in high-enthalpy experiments.\n
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\n \n\n \n \n Brouwer, K. R.; and McNamara, J. J.\n\n\n \n \n \n \n Surrogate-based aeroelastic loads prediction in the presence of shock-induced separation.\n \n \n \n\n\n \n\n\n\n Journal of Fluids and Structures, 93: 102838. February 2020.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
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@article{brouwer2020,\n\ttitle = {Surrogate-based aeroelastic loads prediction in the presence of shock-induced separation},\n\tvolume = {93},\n\tissn = {0889-9746},\n\tdoi = {10.1016/j.jfluidstructs.2019.102838},\n\tabstract = {A surrogate-based modeling strategy is presented for robust and efficient prediction of unsteady aeroelastic loads in the presence of shock-induced separation. Enriched piston theory predictions are extended with a data-driven nonlinear autoregressive with exogenous inputs model to account for hysteresis from the interplay of a dynamically deforming surface with the separation bubble in a shock/boundary layer interaction. The approach is evaluated for prescribed surface motion and shock-induced panel flutter responses, with good agreement observed in each scenario relative to unsteady Reynolds-averaged Navier–Stokes simulations. For the latter, excellent agreement is observed in the prediction of the stability boundary and oscillation frequency. In contrast, the oscillation amplitude conservatively deviates from the Reynolds-averaged Navier–Stokes solution with increasing dynamic pressure. The online computational cost of the extended approach is orders of magnitude less than that required for predictions using an unsteady Reynolds-averaged Navier–Stokes model.},\n\tlanguage = {en},\n\turldate = {2023-08-11},\n\tjournal = {Journal of Fluids and Structures},\n\tauthor = {Brouwer, Kirk R. and McNamara, Jack J.},\n\tmonth = feb,\n\tyear = {2020},\n\tkeywords = {Kriging, Limit cycle oscillation, NARX model, Panel flutter, Shock impingement, Supersonic, Surrogate models, Two-dimensional},\n\tpages = {102838},\n}\n\n\n\n\n\n\n\n
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\n A surrogate-based modeling strategy is presented for robust and efficient prediction of unsteady aeroelastic loads in the presence of shock-induced separation. Enriched piston theory predictions are extended with a data-driven nonlinear autoregressive with exogenous inputs model to account for hysteresis from the interplay of a dynamically deforming surface with the separation bubble in a shock/boundary layer interaction. The approach is evaluated for prescribed surface motion and shock-induced panel flutter responses, with good agreement observed in each scenario relative to unsteady Reynolds-averaged Navier–Stokes simulations. For the latter, excellent agreement is observed in the prediction of the stability boundary and oscillation frequency. In contrast, the oscillation amplitude conservatively deviates from the Reynolds-averaged Navier–Stokes solution with increasing dynamic pressure. The online computational cost of the extended approach is orders of magnitude less than that required for predictions using an unsteady Reynolds-averaged Navier–Stokes model.\n
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\n \n\n \n \n Huang, D.; and Friedmann, P. P.\n\n\n \n \n \n \n An aerothermoelastic analysis framework with reduced-order modeling applied to composite panels in hypersonic flows.\n \n \n \n\n\n \n\n\n\n Journal of Fluids and Structures, 94: 102927. April 2020.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{huang2020,\n\ttitle = {An aerothermoelastic analysis framework with reduced-order modeling applied to composite panels in hypersonic flows},\n\tvolume = {94},\n\tissn = {0889-9746},\n\tdoi = {10.1016/j.jfluidstructs.2020.102927},\n\tabstract = {This study describes the enhancement of a computational framework for aerothermoelasticity using novel model order reduction techniques and efficient coupling schemes. First, the fluid solver for hypersonic aerothermodynamics is accelerated using a reduced order model. The flexibility of the reduced order model is enhanced using a novel correction and scaling technique, which accounts for non-uniform temperature distribution, varying flight conditions and geometrical scales using analytical pointwise models. Secondly, based on the reduced order model, a tightly-coupled scheme and linearized stability analysis are developed for fast aerothermoelastic simulation of extended flight time and automatic identification of aerothermoelastic instabilities, respectively. The enhanced framework is accelerated by a factor of 104 so that near-real-time aerothermoelastic simulation is achieved. Finally, using the enhanced framework, the aerothermoelastic response of a generic skin panel is studied emphasizing the effect of flow orientation angle and material orthotropicity on the aerothermoelastic stability boundary. It is found that a combination of flow orientation angle and material orientation can significantly extend the aerothermoelastic stability boundary, i.e. the time elapsed before the onset of structural failure.},\n\tlanguage = {en},\n\turldate = {2023-08-09},\n\tjournal = {Journal of Fluids and Structures},\n\tauthor = {Huang, Daning and Friedmann, Peretz P.},\n\tmonth = apr,\n\tyear = {2020},\n\tkeywords = {Fluid–thermal-structure interaction, Hypersonic aerothermoelasticity, Linearized stability analysis, Panel flutter, Reduced-order modeling},\n\tpages = {102927},\n}\n\n\n\n
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\n This study describes the enhancement of a computational framework for aerothermoelasticity using novel model order reduction techniques and efficient coupling schemes. First, the fluid solver for hypersonic aerothermodynamics is accelerated using a reduced order model. The flexibility of the reduced order model is enhanced using a novel correction and scaling technique, which accounts for non-uniform temperature distribution, varying flight conditions and geometrical scales using analytical pointwise models. Secondly, based on the reduced order model, a tightly-coupled scheme and linearized stability analysis are developed for fast aerothermoelastic simulation of extended flight time and automatic identification of aerothermoelastic instabilities, respectively. The enhanced framework is accelerated by a factor of 104 so that near-real-time aerothermoelastic simulation is achieved. Finally, using the enhanced framework, the aerothermoelastic response of a generic skin panel is studied emphasizing the effect of flow orientation angle and material orthotropicity on the aerothermoelastic stability boundary. It is found that a combination of flow orientation angle and material orientation can significantly extend the aerothermoelastic stability boundary, i.e. the time elapsed before the onset of structural failure.\n
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\n \n\n \n \n Whalen, T. J.; Schöneich, A. G.; Laurence, S. J.; Sullivan, B. T.; Bodony, D. J.; Freydin, M.; Dowell, E. H.; and Buck, G. M.\n\n\n \n \n \n \n Hypersonic Fluid–Structure Interactions in Compression Corner Shock-Wave/Boundary-Layer Interaction.\n \n \n \n\n\n \n\n\n\n AIAA Journal, 58(9): 4090–4105. 2020.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@article{whalen2020,\n\ttitle = {Hypersonic {Fluid}–{Structure} {Interactions} in {Compression} {Corner} {Shock}-{Wave}/{Boundary}-{Layer} {Interaction}},\n\tvolume = {58},\n\tissn = {0001-1452},\n\tdoi = {10.2514/1.J059152},\n\tabstract = {The fluid–structure interaction of a flexible panel exposed to a ramp-induced shock-wave/boundary-layer interaction (SWBLI) at Mach 6 is investigated experimentally for transitional and turbulent incoming boundary layers. Panel deformations are measured using photogrammetry enabled by a new marker-tracking routine, whereas pressure fluctuations are obtained with fast-response piezoresistive pressure transducers. The significance of aerothermal heating is evident in the nonlinear panel response: enhanced static deformations and frequency shifting are consistent with a temperature differential between the panel and its support structure, which induces compressive thermal strain and flexural softening. Time-domain and modal vibratory behavior are correlated to the SWBLI environment, and shear-layer reattachment near antinodes of certain mode shapes is identified as a source of enhanced panel excitation. Comparison with companion rigid-ramp experiments shows evidence of feedback into the downstream flowfield regime.},\n\tnumber = {9},\n\turldate = {2023-08-03},\n\tjournal = {AIAA Journal},\n\tauthor = {Whalen, Thomas J. and Schöneich, Antonio Giovanni and Laurence, Stuart J. and Sullivan, Bryson T. and Bodony, Daniel J. and Freydin, Maxim and Dowell, Earl H. and Buck, Gregory M.},\n\tyear = {2020},\n\tpages = {4090--4105},\n}\n\n\n\n
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\n The fluid–structure interaction of a flexible panel exposed to a ramp-induced shock-wave/boundary-layer interaction (SWBLI) at Mach 6 is investigated experimentally for transitional and turbulent incoming boundary layers. Panel deformations are measured using photogrammetry enabled by a new marker-tracking routine, whereas pressure fluctuations are obtained with fast-response piezoresistive pressure transducers. The significance of aerothermal heating is evident in the nonlinear panel response: enhanced static deformations and frequency shifting are consistent with a temperature differential between the panel and its support structure, which induces compressive thermal strain and flexural softening. Time-domain and modal vibratory behavior are correlated to the SWBLI environment, and shear-layer reattachment near antinodes of certain mode shapes is identified as a source of enhanced panel excitation. Comparison with companion rigid-ramp experiments shows evidence of feedback into the downstream flowfield regime.\n
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\n \n\n \n \n Sasidharan, V.; and Duvvuri, S.\n\n\n \n \n \n \n Video: Pulsating shock waves at Mach 6.\n \n \n \n\n\n \n\n\n\n In November 2020. American Physical Society (APS)\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@inproceedings{sasidharan2020,\n\ttitle = {Video: {Pulsating} shock waves at {Mach} 6},\n\tdoi = {10.1103/aps.dfd.2020.gfm.v0015},\n\tpublisher = {American Physical Society (APS)},\n\tauthor = {Sasidharan, Vaisakh and Duvvuri, Subrahmanyam},\n\tmonth = nov,\n\tyear = {2020},\n}\n\n\n\n
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\n \n\n \n \n Krish, A.; Streicher, J. W; and Hanson, R. K\n\n\n \n \n \n \n Ultraviolet Absorption Cross-Section Measurements of Shock-Heated O\\textsubscript\\2\\ from 2,000-8,400 K using a Tunable Laser.\n \n \n \n\n\n \n\n\n\n Journal of Quantitative Spectroscopy & Radiative Transfer, 247. 2020.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@article{krish2020,\n\ttitle = {Ultraviolet {Absorption} {Cross}-{Section} {Measurements} of {Shock}-{Heated} {O}{\\textbackslash}textsubscript\\{2\\} from 2,000-8,400 {K} using a {Tunable} {Laser}},\n\tvolume = {247},\n\tjournal = {Journal of Quantitative Spectroscopy \\& Radiative Transfer},\n\tauthor = {Krish, Ajay and Streicher, Jesse W and Hanson, Ronald K},\n\tyear = {2020},\n}\n\n\n\n
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\n \n\n \n \n Chaudhry, R. S; Boyd, I. D; and Candler, G. V\n\n\n \n \n \n \n Vehicle-Scale Simulations of Hypersonic Flows using the MMT Chemical Kinetics Model.\n \n \n \n\n\n \n\n\n\n In June 2020. \\AIAA Paper\\ 2020-3272\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{chaudhry2020,\n\ttitle = {Vehicle-{Scale} {Simulations} of {Hypersonic} {Flows} using the {MMT} {Chemical} {Kinetics} {Model}},\n\tpublisher = {\\{AIAA Paper\\} 2020-3272},\n\tauthor = {Chaudhry, Ross S and Boyd, Iain D and Candler, Graham V},\n\tmonth = jun,\n\tyear = {2020},\n}\n\n\n\n
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\n \n\n \n \n Pegmire, J.\n\n\n \n \n \n \n Tennis players at French Open rattled by sonic boom.\n \n \n \n\n\n \n\n\n\n Associated Press. 2020.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@article{pegmire2020,\n\ttitle = {Tennis players at {French} {Open} rattled by sonic boom},\n\tjournal = {Associated Press},\n\tauthor = {Pegmire, Jermome},\n\tyear = {2020},\n}\n\n\n\n
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\n \n\n \n \n MacDonald, R. L.; Torres, E.; Schwartzentruber, T. E.; and Panesi, M.\n\n\n \n \n \n \n State-to-State Master Equation and Direct Molecular Simulation Study of Energy Transfer and Dissociation for the N2-N System.\n \n \n \n\n\n \n\n\n\n Journal of Physical Chemistry A, 124(35): 6986–7000. September 2020.\n Publisher: American Chemical Society\n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@article{macdonald2020,\n\ttitle = {State-to-{State} {Master} {Equation} and {Direct} {Molecular} {Simulation} {Study} of {Energy} {Transfer} and {Dissociation} for the {N2}-{N} {System}},\n\tvolume = {124},\n\tdoi = {10.1021/ACS.JPCA.0C04029/ASSET/IMAGES/LARGE/JP0C04029_0013.JPEG},\n\tabstract = {We present a detailed comparison of two high-fidelity approaches for simulating non-equilibrium chemical processes in gases: The state-to-state master equation (StS-ME) and the direct molecular simulation (DMS) methods. The former is a deterministic method, which relies on the pre-computed kinetic database for the N2-N system based on the NASA Ames ab initio potential energy surface (PES) to describe the evolution of the molecules' internal energy states through a system of master equations. The latter is a stochastic interpretation of molecular dynamics relying exclusively on the same ab initio PES. It directly tracks the microscopic gas state through a particle ensemble undergoing a sequence of collisions. We study a mixture of nitrogen molecules and atoms forced into strong thermochemical non-equilibrium by sudden exposure of rovibrationally cold gas to a high-temperature heat bath. We observe excellent agreement between the DMS and StS-ME predictions for the transfer rates of translational into rotational and vibrational energy, as well as of dissociation rates across a wide range of temperatures. Both methods agree down to the microscopic scale, where they predict the same non-Boltzmann population distributions during quasi-steady-state dissociation. Beyond establishing the equivalence of both methods, this cross-validation helped in reinterpreting the NASA Ames kinetic database and resolve discrepancies observed in prior studies. The close agreement found between the StS-ME and DMS methods, whose sole model inputs are the PESs, lends confidence to their use as benchmark tools for studying high-temperature air chemistry.},\n\tnumber = {35},\n\tjournal = {Journal of Physical Chemistry A},\n\tauthor = {MacDonald, Robyn L. and Torres, Erik and Schwartzentruber, Thomas E. and Panesi, Marco},\n\tmonth = sep,\n\tyear = {2020},\n\tnote = {Publisher: American Chemical Society},\n\tpages = {6986--7000},\n}\n\n\n\n
\n
\n\n\n
\n We present a detailed comparison of two high-fidelity approaches for simulating non-equilibrium chemical processes in gases: The state-to-state master equation (StS-ME) and the direct molecular simulation (DMS) methods. The former is a deterministic method, which relies on the pre-computed kinetic database for the N2-N system based on the NASA Ames ab initio potential energy surface (PES) to describe the evolution of the molecules' internal energy states through a system of master equations. The latter is a stochastic interpretation of molecular dynamics relying exclusively on the same ab initio PES. It directly tracks the microscopic gas state through a particle ensemble undergoing a sequence of collisions. We study a mixture of nitrogen molecules and atoms forced into strong thermochemical non-equilibrium by sudden exposure of rovibrationally cold gas to a high-temperature heat bath. We observe excellent agreement between the DMS and StS-ME predictions for the transfer rates of translational into rotational and vibrational energy, as well as of dissociation rates across a wide range of temperatures. Both methods agree down to the microscopic scale, where they predict the same non-Boltzmann population distributions during quasi-steady-state dissociation. Beyond establishing the equivalence of both methods, this cross-validation helped in reinterpreting the NASA Ames kinetic database and resolve discrepancies observed in prior studies. The close agreement found between the StS-ME and DMS methods, whose sole model inputs are the PESs, lends confidence to their use as benchmark tools for studying high-temperature air chemistry.\n
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\n \n\n \n \n Liza, M. E.; and Hanquist, K. M.\n\n\n \n \n \n \n Simulation of Hypersonic Flow Fields with Applications to Aero-Optics.\n \n \n \n\n\n \n\n\n\n 2020.\n \n\n\n\n
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@misc{liza2020,\n\taddress = {AIAA  Tucson Section - Technical Mini Conference},\n\ttype = {Conference {Presentation}},\n\ttitle = {Simulation of {Hypersonic} {Flow} {Fields} with {Applications} to {Aero}-{Optics}},\n\tauthor = {Liza, Martin E. and Hanquist, Kyle M.},\n\tyear = {2020},\n\tkeywords = {own, presentation},\n}\n\n\n\n
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\n \n\n \n \n Streicher, J. W.; Krish, A.; Hanson, R. K.; Hanquist, K. M.; Chaudhry, R. S.; and Boyd, I. D.\n\n\n \n \n \n \n Shock-tube measurements of coupled vibration-dissociation time-histories and rate parameters in oxygen and argon mixtures from 5000 K to 10 000 K.\n \n \n \n\n\n \n\n\n\n Physics of Fluids, 32(7): 1–21. 2020.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n  \n \n 1 download\n \n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n\n\n\n
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@article{streicher2020,\n\ttitle = {Shock-tube measurements of coupled vibration-dissociation time-histories and rate parameters in oxygen and argon mixtures from 5000 {K} to 10 000 {K}},\n\tvolume = {32},\n\tdoi = {10.1063/5.0012426},\n\tabstract = {Shock-tube experiments were conducted behind reflected shocks using ultraviolet (UV) laser absorption to measure coupled vibration-dissociation (CVDV) time-histories and rate parameters in dilute mixtures of oxygen (O2) and argon (Ar). Experiments probed 2\\% and 5\\% O2 in Ar mixtures for initial post-reflected-shock conditions from 5000 K to 10 000 K and 0.04 atm to 0.45 atm. A tunable, pulsed UV laser absorption diagnostic measured absorbance time-histories from the fourth, fifth, and sixth vibrational levels of the electronic ground state of O2, and experiments were repeated - with closely matched temperature and pressure conditions - to probe absorbance time-histories corresponding to each vibrational level. The absorbance ratio from two vibrational levels, interpreted via an experimentally validated spectroscopic model, determined vibrational temperature time-histories. In contrast, the absorbance involving a single vibrational level determined vibrational-state-specific number density time-histories. These temperature and state-specific number density time-histories agree reasonably well with state-to-state modeling at low temperatures but deviate significantly at high temperatures. Further analysis of the vibrational temperature and number density time-histories isolated coupling parameters from the Marrone and Treanor CVDV model, including vibrational relaxation time (τ), average vibrational energy loss (ϵ), vibrational coupling factor (Z), and dissociation rate constant (kd). The results for τ and kd are consistent with previous results, exhibit low scatter, and - in the case of vibrational relaxation time - extend measurements to higher temperatures than previous experiments. The results for ϵ and Z overlap some common models, exhibit relatively low scatter, and provide novel experimental data.},\n\tnumber = {7},\n\tjournal = {Physics of Fluids},\n\tauthor = {Streicher, Jesse W. and Krish, Ajay and Hanson, Ronald K. and Hanquist, Kyle M. and Chaudhry, Ross S. and Boyd, Iain D.},\n\tyear = {2020},\n\tkeywords = {own},\n\tpages = {1--21},\n}\n\n\n\n
\n
\n\n\n
\n Shock-tube experiments were conducted behind reflected shocks using ultraviolet (UV) laser absorption to measure coupled vibration-dissociation (CVDV) time-histories and rate parameters in dilute mixtures of oxygen (O2) and argon (Ar). Experiments probed 2% and 5% O2 in Ar mixtures for initial post-reflected-shock conditions from 5000 K to 10 000 K and 0.04 atm to 0.45 atm. A tunable, pulsed UV laser absorption diagnostic measured absorbance time-histories from the fourth, fifth, and sixth vibrational levels of the electronic ground state of O2, and experiments were repeated - with closely matched temperature and pressure conditions - to probe absorbance time-histories corresponding to each vibrational level. The absorbance ratio from two vibrational levels, interpreted via an experimentally validated spectroscopic model, determined vibrational temperature time-histories. In contrast, the absorbance involving a single vibrational level determined vibrational-state-specific number density time-histories. These temperature and state-specific number density time-histories agree reasonably well with state-to-state modeling at low temperatures but deviate significantly at high temperatures. Further analysis of the vibrational temperature and number density time-histories isolated coupling parameters from the Marrone and Treanor CVDV model, including vibrational relaxation time (τ), average vibrational energy loss (ϵ), vibrational coupling factor (Z), and dissociation rate constant (kd). The results for τ and kd are consistent with previous results, exhibit low scatter, and - in the case of vibrational relaxation time - extend measurements to higher temperatures than previous experiments. The results for ϵ and Z overlap some common models, exhibit relatively low scatter, and provide novel experimental data.\n
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\n \n\n \n \n Loseille, A.; and Menier, V.\n\n\n \n \n \n \n \n PyAMG.\n \n \n \n \n\n\n \n\n\n\n 2020.\n \n\n\n\n
\n\n\n\n \n \n \"PyAMGPaper\n  \n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@misc{loseille2020,\n\ttitle = {{PyAMG}},\n\turl = {https://pyamg.saclay.inria.fr},\n\tauthor = {Loseille, A. and Menier, V.},\n\tyear = {2020},\n}\n\n\n\n
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\n \n\n \n \n Flora, G; Karimzadeh, F; Yamada, T; Grinstead, K D; Kahandawala, M S P; Valentini, P; Grover, M S; Adamovich, I. V; Carter, C D; and Josyula, E\n\n\n \n \n \n \n On characterizing nonequilibrium at the shock-front in shock tube experiments with pure oxygen.\n \n \n \n\n\n \n\n\n\n In Orlando, FL, January 2020. \\AIAA Paper\\ 2020-0621\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{flora2020,\n\taddress = {Orlando, FL},\n\ttitle = {On characterizing nonequilibrium at the shock-front in shock tube experiments with pure oxygen},\n\tpublisher = {\\{AIAA Paper\\} 2020-0621},\n\tauthor = {Flora, G and Karimzadeh, F and Yamada, T and Grinstead, K D and Kahandawala, M S P and Valentini, P and Grover, M S and Adamovich, Igor V and Carter, C D and Josyula, E},\n\tmonth = jan,\n\tyear = {2020},\n}\n\n\n\n
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\n \n\n \n \n Garbacz, C.; Fossati, M.; Maier, W. T; Alanso, J. J; Scoggins, J. B; Economon, T. D; and Magin, T. E\n\n\n \n \n \n \n Numerical Study of Shock Interference Patterns for Gas Flows with Thermal Nonequilibrium and Finite-Rate Chemistry.\n \n \n \n\n\n \n\n\n\n In 2020. \\AIAA Paper\\ 2020-1805\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@inproceedings{garbacz2020,\n\ttitle = {Numerical {Study} of {Shock} {Interference} {Patterns} for {Gas} {Flows} with {Thermal} {Nonequilibrium} and {Finite}-{Rate} {Chemistry}},\n\tdoi = {10.2514/6.2020-1805},\n\tpublisher = {\\{AIAA Paper\\} 2020-1805},\n\tauthor = {Garbacz, Catrina and Fossati, Marco and Maier, Walter T and Alanso, Juan J and Scoggins, James B and Economon, Thomas D and Magin, Thierry E},\n\tyear = {2020},\n}\n\n\n\n
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\n \n\n \n \n Linstrom, P J; and Mallard, W G,\n editors.\n \n\n\n \n \n \n \n \n NIST Chemistry WebBook, NIST Standard Reference Database Number 69.\n \n \n \n \n\n\n \n\n\n\n . 2020.\n Publisher: National Institute of Standards and Technology,\n\n\n\n
\n\n\n\n \n \n \"NISTPaper\n  \n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@article{linstrom2020,\n\ttitle = {{NIST} {Chemistry} {WebBook}, {NIST} {Standard} {Reference} {Database} {Number} 69},\n\turl = {https://doi.org/10.18434/T4D303},\n\teditor = {Linstrom, P J and Mallard, W G},\n\tyear = {2020},\n\tnote = {Publisher: National Institute of Standards and Technology,},\n}\n\n\n\n
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\n \n\n \n \n Hanquist, K. M.\n\n\n \n \n \n \n Need for Speed: Hypersonic Flight.\n \n \n \n\n\n \n\n\n\n 2020.\n \n\n\n\n
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@misc{hanquist2020,\n\taddress = {Mechanical, Aerospace, and Biomedical Engineering Department, University of Tennessee-Knoxville},\n\ttype = {Invited {Seminar}},\n\ttitle = {Need for {Speed}: {Hypersonic} {Flight}},\n\tauthor = {Hanquist, Kyle M.},\n\tyear = {2020},\n\tkeywords = {invited, own},\n}\n\n\n\n
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\n \n\n \n \n Scoggins, J. B.; Leroy, V.; Bellas-Chatzigeorgis, G.; Dias, B.; and Magin, T. E.\n\n\n \n \n \n \n Mutation++: MUlticomponent Thermodynamic And Transport properties for IONized gases in C++.\n \n \n \n\n\n \n\n\n\n SoftwareX, 12: 100575. July 2020.\n arXiv: 2002.01783 Publisher: Elsevier B.V.\n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n\n\n\n
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@article{scoggins2020,\n\ttitle = {Mutation++: {MUlticomponent} {Thermodynamic} {And} {Transport} properties for {IONized} gases in {C}++},\n\tvolume = {12},\n\tissn = {23527110},\n\tdoi = {10.1016/j.softx.2020.100575},\n\tabstract = {The Mutation++ library provides accurate and efficient computation of physicochemical properties associated with partially ionized gases in various degrees of thermal nonequilibrium. With v1.0.0, users can compute thermodynamic and transport properties, multiphase linearly-constrained equilibria, chemical production rates, energy transfer rates, and gas-surface interactions. The framework is based on an object-oriented design in C++, allowing users to plug-and-play various models, algorithms, and data as necessary. Mutation++ is available open-source under the GNU Lesser General Public License v3.0.},\n\turldate = {2021-02-23},\n\tjournal = {SoftwareX},\n\tauthor = {Scoggins, James B. and Leroy, Vincent and Bellas-Chatzigeorgis, Georgios and Dias, Bruno and Magin, Thierry E.},\n\tmonth = jul,\n\tyear = {2020},\n\tnote = {arXiv: 2002.01783\nPublisher: Elsevier B.V.},\n\tkeywords = {Gas-surface interaction, Multiphase equilibrium, Partially ionized gases, Thermochemical nonequilibrium},\n\tpages = {100575},\n}\n\n\n\n
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\n The Mutation++ library provides accurate and efficient computation of physicochemical properties associated with partially ionized gases in various degrees of thermal nonequilibrium. With v1.0.0, users can compute thermodynamic and transport properties, multiphase linearly-constrained equilibria, chemical production rates, energy transfer rates, and gas-surface interactions. The framework is based on an object-oriented design in C++, allowing users to plug-and-play various models, algorithms, and data as necessary. Mutation++ is available open-source under the GNU Lesser General Public License v3.0.\n
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\n \n\n \n \n Scoggins, J. B.; Leroy, V.; Bellas-Chatzigeorgis, G.; Dias, B.; and Magin, T. E.\n\n\n \n \n \n \n Mutation++: MUlticomponent Thermodynamic And Transport properties for IONized gases in C++.\n \n \n \n\n\n \n\n\n\n SoftwareX, 12: 100575–100575. July 2020.\n Publisher: Elsevier B.V.\n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n\n\n\n
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@article{scoggins2020a,\n\ttitle = {Mutation++: {MUlticomponent} {Thermodynamic} {And} {Transport} properties for {IONized} gases in {C}++},\n\tvolume = {12},\n\tdoi = {10.1016/j.softx.2020.100575},\n\tabstract = {The Mutation++ library provides accurate and efficient computation of physicochemical properties associated with partially ionized gases in various degrees of thermal nonequilibrium. With v1.0.0, users can compute thermodynamic and transport properties, multiphase linearly-constrained equilibria, chemical production rates, energy transfer rates, and gas-surface interactions. The framework is based on an object-oriented design in C++, allowing users to plug-and-play various models, algorithms, and data as necessary. Mutation++ is available open-source under the GNU Lesser General Public License v3.0.},\n\tjournal = {SoftwareX},\n\tauthor = {Scoggins, James B. and Leroy, Vincent and Bellas-Chatzigeorgis, Georgios and Dias, Bruno and Magin, Thierry E.},\n\tmonth = jul,\n\tyear = {2020},\n\tnote = {Publisher: Elsevier B.V.},\n\tkeywords = {Gas-surface interaction, Multiphase equilibrium, Partially ionized gases, Thermochemical nonequilibrium},\n\tpages = {100575--100575},\n}\n\n\n\n
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\n The Mutation++ library provides accurate and efficient computation of physicochemical properties associated with partially ionized gases in various degrees of thermal nonequilibrium. With v1.0.0, users can compute thermodynamic and transport properties, multiphase linearly-constrained equilibria, chemical production rates, energy transfer rates, and gas-surface interactions. The framework is based on an object-oriented design in C++, allowing users to plug-and-play various models, algorithms, and data as necessary. Mutation++ is available open-source under the GNU Lesser General Public License v3.0.\n
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\n \n\n \n \n Scoggins, J. B; Leroy, V.; Bellas-Chatzigeorgis, G.; Dias, B.; and Magin, T. E\n\n\n \n \n \n \n Mutation${\\textasciicircum}\\{++\\}$: MUlticomponent Thermodynamic And Transport properties for IONized gases in C$++$.\n \n \n \n\n\n \n\n\n\n SoftwareX, 12. 2020.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@article{scoggins2020b,\n\ttitle = {Mutation\\${\\textasciicircum}\\{++\\}\\$: {MUlticomponent} {Thermodynamic} {And} {Transport} properties for {IONized} gases in {C}\\$++\\$},\n\tvolume = {12},\n\tdoi = {10.1016/j.softx.2020.100575},\n\tjournal = {SoftwareX},\n\tauthor = {Scoggins, James B and Leroy, Vincent and Bellas-Chatzigeorgis, Georgios and Dias, Bruno and Magin, Thierry E},\n\tyear = {2020},\n}\n\n\n\n
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\n \n\n \n \n Hanquist, K. M.; Düzel, Ü.; Liza, M. E.; Sadagopan, A.; and Huang, D.\n\n\n \n \n \n \n Modeling High-Temperature Flow Field Effects Relevant to Fluid-Thermal-Structural Interactions.\n \n \n \n\n\n \n\n\n\n In Joint Meeting of the Combustion, Airbreathing Propulsion, Exhaust Plume and Signatures, and Energetic Systems Hazards subcommittees, and Programmatic and Industrial Base meeting, 2020. JANNAF\n \n\n\n\n
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@inproceedings{hanquist2020i,\n\ttitle = {Modeling {High}-{Temperature} {Flow} {Field} {Effects} {Relevant} to {Fluid}-{Thermal}-{Structural} {Interactions}},\n\tbooktitle = {Joint {Meeting} of the {Combustion}, {Airbreathing} {Propulsion}, {Exhaust} {Plume} and {Signatures}, and {Energetic} {Systems} {Hazards} subcommittees, and {Programmatic} and {Industrial} {Base} meeting},\n\tpublisher = {JANNAF},\n\tauthor = {Hanquist, Kyle M. and Düzel, Ümran and Liza, Martin E. and Sadagopan, Aravinth and Huang, Daning},\n\tyear = {2020},\n\tkeywords = {own},\n}\n\n\n\n
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\n \n\n \n \n Tropina, A. A; Wu, Y.; Limbach, C. M; and Miles, R. B\n\n\n \n \n \n \n \n Influence of vibrational non-equilibrium on the polarizability and refraction index in air: computational study.\n \n \n \n \n\n\n \n\n\n\n Journal of Physics D: Applied Physics, 53(10): 105201. March 2020.\n \n\n\n\n
\n\n\n\n \n \n \"InfluencePaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{tropina2020a,\n\ttitle = {Influence of vibrational non-equilibrium on the polarizability and refraction index in air: computational study},\n\tvolume = {53},\n\tissn = {0022-3727, 1361-6463},\n\tshorttitle = {Influence of vibrational non-equilibrium on the polarizability and refraction index in air},\n\turl = {https://iopscience.iop.org/article/10.1088/1361-6463/ab5bb2},\n\tdoi = {10.1088/1361-6463/ab5bb2},\n\tabstract = {Knowledge of optical effects accompanying hypersonic flight conditions is of critical importance to ensure reliable operation of on-board optical instrumentation. This paper presents results of calculations of scalar polarizability dependence on vibrational nonequilibrium in molecular nitrogen and oxygen. The non-equilibrium effects are evaluated on the basis of a semi-classical model for the molecular polarizability. It is shown that, depending on the vibrational and translational populations, changes in the scalar polarizability in excess of normal density and temperature scaling can be around 1\\%–5\\% at moderate gas temperatures and around 10\\% at high temperatures. The model was applied to predict the polarizability for non-equilibrium states in a nitrogen plasma formed by a single nanosecond pulse with different rise times.},\n\tlanguage = {en},\n\tnumber = {10},\n\turldate = {2023-05-04},\n\tjournal = {Journal of Physics D: Applied Physics},\n\tauthor = {Tropina, Albina A and Wu, Yue and Limbach, Christopher M and Miles, Richard B},\n\tmonth = mar,\n\tyear = {2020},\n\tpages = {105201},\n}\n\n\n\n
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\n Knowledge of optical effects accompanying hypersonic flight conditions is of critical importance to ensure reliable operation of on-board optical instrumentation. This paper presents results of calculations of scalar polarizability dependence on vibrational nonequilibrium in molecular nitrogen and oxygen. The non-equilibrium effects are evaluated on the basis of a semi-classical model for the molecular polarizability. It is shown that, depending on the vibrational and translational populations, changes in the scalar polarizability in excess of normal density and temperature scaling can be around 1%–5% at moderate gas temperatures and around 10% at high temperatures. The model was applied to predict the polarizability for non-equilibrium states in a nitrogen plasma formed by a single nanosecond pulse with different rise times.\n
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\n \n\n \n \n Chaudhry, R. S; Boyd, I. D; Torres, E.; Schwartzentruber, T. E; and Candler, G.\n\n\n \n \n \n \n Implementation of a Chemical Kinetics Model for Hypersonic Flows in Air for High-Performance CFD.\n \n \n \n\n\n \n\n\n\n In Orlando, FL, January 2020. \\AIAA Paper\\ 2020-2191\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{chaudhry2020a,\n\taddress = {Orlando, FL},\n\ttitle = {Implementation of a {Chemical} {Kinetics} {Model} for {Hypersonic} {Flows} in {Air} for {High}-{Performance} {CFD}},\n\tpublisher = {\\{AIAA Paper\\} 2020-2191},\n\tauthor = {Chaudhry, Ross S and Boyd, Iain D and Torres, Erik and Schwartzentruber, Thomas E and Candler, Graham},\n\tmonth = jan,\n\tyear = {2020},\n}\n\n\n\n
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\n \n\n \n \n Morin, A. J; Osborn, R.; Schindler, J. C; Jagun, P.; Fletcher, D. G; and Meyers, J. M\n\n\n \n \n \n \n Inductively Coupled Facility Qualification for Electron Transpiration Cooling Investigations.\n \n \n \n\n\n \n\n\n\n In Orlando, FL, January 2020. \\AIAA Paper\\ 2020-0921\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n\n\n\n
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@inproceedings{morin2020,\n\taddress = {Orlando, FL},\n\ttitle = {Inductively {Coupled} {Facility} {Qualification} for {Electron} {Transpiration} {Cooling} {Investigations}},\n\tpublisher = {\\{AIAA Paper\\} 2020-0921},\n\tauthor = {Morin, Andrew J and Osborn, Rebecca and Schindler, Jeff C and Jagun, Precious and Fletcher, Douglas G and Meyers, Jason M},\n\tmonth = jan,\n\tyear = {2020},\n\tkeywords = {etc},\n}\n\n\n\n
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\n \n\n \n \n Vogiatzis, K.; Munafò, A.; Panesi, M.; Vedula, P.; and Josyula, E.\n\n\n \n \n \n \n HyperCode: A framework for high-order accurate turbulent non-equilibrium hypersonic flow simulations.\n \n \n \n\n\n \n\n\n\n In Orlando, FL, January 2020. AIAA 2020-2192\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@inproceedings{vogiatzis2020,\n\taddress = {Orlando, FL},\n\ttitle = {{HyperCode}: {A} framework for high-order accurate turbulent non-equilibrium hypersonic flow simulations},\n\tpublisher = {AIAA 2020-2192},\n\tauthor = {Vogiatzis, Konstantinos and Munafò, Alessandro and Panesi, Marco and Vedula, Prakash and Josyula, Eswar},\n\tmonth = jan,\n\tyear = {2020},\n}\n\n\n\n
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\n \n\n \n \n Parent, B.; Omprakas, A.; and Hanquist, K. M.\n\n\n \n \n \n \n Fully-Coupled Simulation of Plasma Discharges, Turbulence, and Combustion in a Scramjet Combustor.\n \n \n \n\n\n \n\n\n\n In AIAA Aviation and Aeronautics Forum and Exposition, 2020. AIAA Paper 2020-3230\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n  \n \n 3 downloads\n \n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n\n\n\n
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@inproceedings{parent2020b,\n\ttitle = {Fully-{Coupled} {Simulation} of {Plasma} {Discharges}, {Turbulence}, and {Combustion} in a {Scramjet} {Combustor}},\n\tdoi = {10.2514/6.2020-3230},\n\tabstract = {Simulating plasma-assisted combustion represents a considerable challenge due to the large discrepancy of the time scales involved. While the turbulent eddy time scales are of the order of microseconds, the plasma sheath time scales are 3-4 orders of magnitude lower. Contrarily to the chemical reactions, the stiffness of the plasma equations can not be relieved simply by using an implicit integration strategy, thus leading to excessive computational effort even for the simplest cases. Recently, it was shown that this hurdle can be overcome by recasting the plasma driftdiffusion transport equations such that the potential is not obtained from Gauss’s law directly but rather from Ohm’s law. Such a recast is performed while still ensuring that Gauss’s law is satisfied and thus does not modify the physics of the drift-diffusion model in any way. In this paper, we use this novel approach to integrate, for the first time, a plasma discharge in fully coupled form with the turbulent hydrogen/air mixing layer and combustion process taking place in the combustor of a scramjet flying at Mach 11. The chemical model includes electrons, 7 different types of ions, 11 neutral species and 79 reactions. Results indicate that more than 5 discharges need to be performed before achieving a self-repeating pattern due to the strong coupling between the flow, combustion, and plasma. Further, the plasma-assisted flame anchoring is seen to create a recirculation region of significant size within the turbulent boundary layer which affects skin friction and heat loads considerably.},\n\tbooktitle = {{AIAA} {Aviation} and {Aeronautics} {Forum} and {Exposition}},\n\tpublisher = {AIAA Paper 2020-3230},\n\tauthor = {Parent, Bernard and Omprakas, Ajjay and Hanquist, Kyle M.},\n\tyear = {2020},\n\tkeywords = {own},\n}\n\n\n\n
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\n Simulating plasma-assisted combustion represents a considerable challenge due to the large discrepancy of the time scales involved. While the turbulent eddy time scales are of the order of microseconds, the plasma sheath time scales are 3-4 orders of magnitude lower. Contrarily to the chemical reactions, the stiffness of the plasma equations can not be relieved simply by using an implicit integration strategy, thus leading to excessive computational effort even for the simplest cases. Recently, it was shown that this hurdle can be overcome by recasting the plasma driftdiffusion transport equations such that the potential is not obtained from Gauss’s law directly but rather from Ohm’s law. Such a recast is performed while still ensuring that Gauss’s law is satisfied and thus does not modify the physics of the drift-diffusion model in any way. In this paper, we use this novel approach to integrate, for the first time, a plasma discharge in fully coupled form with the turbulent hydrogen/air mixing layer and combustion process taking place in the combustor of a scramjet flying at Mach 11. The chemical model includes electrons, 7 different types of ions, 11 neutral species and 79 reactions. Results indicate that more than 5 discharges need to be performed before achieving a self-repeating pattern due to the strong coupling between the flow, combustion, and plasma. Further, the plasma-assisted flame anchoring is seen to create a recirculation region of significant size within the turbulent boundary layer which affects skin friction and heat loads considerably.\n
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\n \n\n \n \n Fields, N.\n\n\n \n \n \n \n \n Fact Sheet - Supersonic Flight.\n \n \n \n \n\n\n \n\n\n\n Technical Report 2020.\n \n\n\n\n
\n\n\n\n \n \n \"FactPaper\n  \n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@techreport{fields2020,\n\ttitle = {Fact {Sheet} - {Supersonic} {Flight}},\n\turl = {https://www.faa.gov/news/fact_sheets/news_story.cfm?newsId=22754},\n\tauthor = {Fields, NIa},\n\tyear = {2020},\n}\n\n\n\n
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\n \n\n \n \n Bellas-Chatzigeorgis, G.; Magin, T. E.; and Barbante, P. F.\n\n\n \n \n \n \n Energy accommodation coefficient calculation methodology using state-to-state catalysis applied to hypersonic flows.\n \n \n \n\n\n \n\n\n\n AIAA Journal, 58(1): 278–290. November 2020.\n Publisher: AIAA International\n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
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@article{bellas-chatzigeorgis2020,\n\ttitle = {Energy accommodation coefficient calculation methodology using state-to-state catalysis applied to hypersonic flows},\n\tvolume = {58},\n\tdoi = {10.2514/1.J058543},\n\tabstract = {The interplay of a gas–surface interaction and thermal nonequilibrium is still an open problem in aerothermodynamics. In the case of reusable thermal protection systems, it is unclear how much of the recombination energy is stored internally in the molecules produced by surface catalytic reactions, potentially leading to nonequilibrium between their translational and internal energy modes. A methodology is developed to calculate the energy accommodation coefficient using a rovibrational state-to-state chemical mechanism for a nitrogen mixture coupled with a generalized form of the catalytic recombination coefficient. The flow around a spherical body is simulated in hypersonic conditions, allowing study of the amount of energy deposited on the surface and stored in the recombining molecules. Internal energy quenching into translational energy is found, which is a phenomenon also observed experimentally, keeping the total energy transferred to the surface overall constant. The methodology developed for the application of a state-to-state model in the computational fluid dynamics framework coupled with catalysis is generic and applicable to a variety of other similar mechanisms.},\n\tnumber = {1},\n\tjournal = {AIAA Journal},\n\tauthor = {Bellas-Chatzigeorgis, Georgios and Magin, Thierry E. and Barbante, Paolo F.},\n\tmonth = nov,\n\tyear = {2020},\n\tnote = {Publisher: AIAA International},\n\tkeywords = {Aerothermodynamics, Chemical Equilibrium, Computational Fluid Dynamics, Freestream Conditions, Heterogeneous Catalysis, Hypersonic Flows, Quenching, Thermal Nonequilibrium, Thermal Protection System, Vibrational Energy},\n\tpages = {278--290},\n}\n\n\n\n
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\n The interplay of a gas–surface interaction and thermal nonequilibrium is still an open problem in aerothermodynamics. In the case of reusable thermal protection systems, it is unclear how much of the recombination energy is stored internally in the molecules produced by surface catalytic reactions, potentially leading to nonequilibrium between their translational and internal energy modes. A methodology is developed to calculate the energy accommodation coefficient using a rovibrational state-to-state chemical mechanism for a nitrogen mixture coupled with a generalized form of the catalytic recombination coefficient. The flow around a spherical body is simulated in hypersonic conditions, allowing study of the amount of energy deposited on the surface and stored in the recombining molecules. Internal energy quenching into translational energy is found, which is a phenomenon also observed experimentally, keeping the total energy transferred to the surface overall constant. The methodology developed for the application of a state-to-state model in the computational fluid dynamics framework coupled with catalysis is generic and applicable to a variety of other similar mechanisms.\n
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\n \n\n \n \n Hanquist, K. M.\n\n\n \n \n \n \n \n Detailed Investigation of Nonequilibrium Effects on Aero-Optics in Hypersonic Flows.\n \n \n \n \n\n\n \n\n\n\n Technical Report University of Arizona - Air Force Research Laboratory, 2020.\n \n\n\n\n
\n\n\n\n \n \n \"DetailedPaper\n  \n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@techreport{hanquist2020g,\n\ttitle = {Detailed {Investigation} of {Nonequilibrium} {Effects} on {Aero}-{Optics} in {Hypersonic} {Flows}},\n\turl = {https://chanl.arizona.edu/afrl-final-report-2020},\n\tinstitution = {University of Arizona - Air Force Research Laboratory},\n\tauthor = {Hanquist, Kyle M.},\n\tyear = {2020},\n}\n\n\n\n
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\n \n\n \n \n Hanquist, K. M.; Chaudhry, R. S.; Boyd, I. D.; Streicher, J. W.; Krish, A.; and Hanson, R. K.\n\n\n \n \n \n \n Detailed Thermochemical Modeling of O$_{\\textrm{2}}$-Ar in Reflected Shock Tube Flows.\n \n \n \n\n\n \n\n\n\n In AIAA Aviation and Aeronautics Forum and Exposition, 2020. AIAA Paper 2020-3275\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n\n\n\n
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@inproceedings{hanquist2020h,\n\ttitle = {Detailed {Thermochemical} {Modeling} of {O}$_{\\textrm{2}}$-{Ar} in {Reflected} {Shock} {Tube} {Flows}},\n\tdoi = {10.2514/6.2020-3275},\n\tabstract = {Simulation results are presented of a set of vibrational nonequilibrium models with a range of fidelity and are compared to experimental data for several post-normal reflected shock test cases of O2-Ar mixtures. Three different modeling approaches with a range of fidelity are used to determine the vibrational nonequilibrium of the post-normal shock flows. The twotemperature (2T) model is the widely used approach for hypersonic analysis and is presented as the computationally efficient, lower fidelity modeling approach in this work. In contrast, the full state-to-state (STS) model, a master equation approach for each vibrational state, is presented as the higher fidelity modeling approach. Both approaches have several available methods for obtaining rate data that are investigated. The STS approach uses rate data from the forced harmonic oscillator (FHO) approach and quasi-classical trajectory analysis (QCT) for the O2-Ar, O2-O, and O2-O2 systems. The simulated vibrational temperatures and state-specific vibrational level concentrations are compared to experimental measurements. The experimental measurements have a low level of uncertainty and allow for insight into the performance of the nonequilibrium modeling. A rate sensitivity study is also completed that shows how sensitive the results are to certain rates at each experimental condition.},\n\tbooktitle = {{AIAA} {Aviation} and {Aeronautics} {Forum} and {Exposition}},\n\tpublisher = {AIAA Paper 2020-3275},\n\tauthor = {Hanquist, Kyle M. and Chaudhry, Ross S. and Boyd, Iain D. and Streicher, Jesse W. and Krish, Ajay and Hanson, Ronald K.},\n\tyear = {2020},\n\tkeywords = {own},\n}\n\n\n\n
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\n Simulation results are presented of a set of vibrational nonequilibrium models with a range of fidelity and are compared to experimental data for several post-normal reflected shock test cases of O2-Ar mixtures. Three different modeling approaches with a range of fidelity are used to determine the vibrational nonequilibrium of the post-normal shock flows. The twotemperature (2T) model is the widely used approach for hypersonic analysis and is presented as the computationally efficient, lower fidelity modeling approach in this work. In contrast, the full state-to-state (STS) model, a master equation approach for each vibrational state, is presented as the higher fidelity modeling approach. Both approaches have several available methods for obtaining rate data that are investigated. The STS approach uses rate data from the forced harmonic oscillator (FHO) approach and quasi-classical trajectory analysis (QCT) for the O2-Ar, O2-O, and O2-O2 systems. The simulated vibrational temperatures and state-specific vibrational level concentrations are compared to experimental measurements. The experimental measurements have a low level of uncertainty and allow for insight into the performance of the nonequilibrium modeling. A rate sensitivity study is also completed that shows how sensitive the results are to certain rates at each experimental condition.\n
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\n \n\n \n \n Hanquist, K. M.\n\n\n \n \n \n \n \n Detailed Investigation of Nonequilibrium Effects on Aero-Optics in Hypersonic Flows.\n \n \n \n \n\n\n \n\n\n\n Technical Report 2020.\n \n\n\n\n
\n\n\n\n \n \n \"DetailedPaper\n  \n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@techreport{hanquist2020f,\n\ttitle = {Detailed {Investigation} of {Nonequilibrium} {Effects} on {Aero}-{Optics} in {Hypersonic} {Flows}},\n\turl = {https://chanl.arizona.edu/afrl-final-report-2020},\n\tauthor = {Hanquist, Kyle M.},\n\tyear = {2020},\n}\n\n\n\n
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\n \n\n \n \n Gardner, L.\n\n\n \n \n \n \n Covid-19 has Forced Higher Ed to Pivot to Online Learning. Here are 7 Takeaways so Far.\n \n \n \n\n\n \n\n\n\n The Chronicle of Higher Education. 2020.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@article{gardner2020,\n\ttitle = {Covid-19 has {Forced} {Higher} {Ed} to {Pivot} to {Online} {Learning}. {Here} are 7 {Takeaways} so {Far}.},\n\tjournal = {The Chronicle of Higher Education},\n\tauthor = {Gardner, L.},\n\tyear = {2020},\n}\n\n\n\n
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\n \n\n \n \n Hanquist, K. M; and Liza, M. E\n\n\n \n \n \n \n Detailed Investigation of Nonequilibrium Effects on Aero-Optics in Hypersonic Flows.\n \n \n \n\n\n \n\n\n\n Technical Report September 2020.\n \n\n\n\n
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@techreport{hanquist2020c,\n\ttitle = {Detailed {Investigation} of {Nonequilibrium} {Effects} on {Aero}-{Optics} in {Hypersonic} {Flows}},\n\tauthor = {Hanquist, Kyle M and Liza, Martin E},\n\tmonth = sep,\n\tyear = {2020},\n}\n\n\n\n
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\n \n\n \n \n Brune, A. J.; West, T. K.; and Whit, L. M.\n\n\n \n \n \n \n Calibration probe uncertainty and validation for the hypersonic material environmental test system.\n \n \n \n\n\n \n\n\n\n Journal of Thermophysics and Heat Transfer, 34(2): 404–420. January 2020.\n Publisher: American Institute of Aeronautics and Astronautics Inc.\n\n\n\n
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@article{brune2020,\n\ttitle = {Calibration probe uncertainty and validation for the hypersonic material environmental test system},\n\tvolume = {34},\n\tdoi = {10.2514/1.T5839},\n\tabstract = {This paper presents an uncertainty analysis of the stagnation-point calibration probe surface predictions for conditions that span the performance envelope of the Hypersonic Materials Environmental Test System facility located at NASA Langley Research Center. A second-order stochastic expansion was constructed over 47 uncertain parameters to evaluate the sensitivities, identify the most significant uncertain variables, and quantify the uncertainty in the stagnation-point heat flux and pressure predictions of the calibration probe for low- and high-enthalpy test conditions. A sensitivity analysis showed that measurement bias uncertainty is the most significant contributor to the stagnation-point pressure and heat flux variance for the low-enthalpy condition. For the high-enthalpy condition, a paradigm shift in sensitivities revealed the computational fluid dynamics model input uncertainty as the main contributor. A comparison between the prediction and measurement of the stagnation-point conditions under uncertainty showed that there was evidence of statistical disagreement. A validation metric was proposed and applied to the prediction uncertainty to account for the statistical disagreement when compared with the possible stagnation-point heat flux and pressure measurements.},\n\tnumber = {2},\n\tjournal = {Journal of Thermophysics and Heat Transfer},\n\tauthor = {Brune, Andrew J. and West, Thomas K. and Whit, Laura M.},\n\tmonth = jan,\n\tyear = {2020},\n\tnote = {Publisher: American Institute of Aeronautics and Astronautics Inc.},\n\tkeywords = {CFD Simulation, Collocation Method, Cumulative Distribution Function, Enthalpy, Heat Flux, NASA Langley Research Center, Sensitivity Analysis, Slug Calorimeters, Stagnation Pressure, Thermal Protection System},\n\tpages = {404--420},\n}\n\n\n\n
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\n This paper presents an uncertainty analysis of the stagnation-point calibration probe surface predictions for conditions that span the performance envelope of the Hypersonic Materials Environmental Test System facility located at NASA Langley Research Center. A second-order stochastic expansion was constructed over 47 uncertain parameters to evaluate the sensitivities, identify the most significant uncertain variables, and quantify the uncertainty in the stagnation-point heat flux and pressure predictions of the calibration probe for low- and high-enthalpy test conditions. A sensitivity analysis showed that measurement bias uncertainty is the most significant contributor to the stagnation-point pressure and heat flux variance for the low-enthalpy condition. For the high-enthalpy condition, a paradigm shift in sensitivities revealed the computational fluid dynamics model input uncertainty as the main contributor. A comparison between the prediction and measurement of the stagnation-point conditions under uncertainty showed that there was evidence of statistical disagreement. A validation metric was proposed and applied to the prediction uncertainty to account for the statistical disagreement when compared with the possible stagnation-point heat flux and pressure measurements.\n
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\n \n\n \n \n Holloway, M. E.; Hanquist, K. M.; and Boyd, I. D.\n\n\n \n \n \n \n Assessment of Thermochemistry Modeling for Hypersonic Flow over a Double Cone.\n \n \n \n\n\n \n\n\n\n Journal of Thermophysics and Heat Transfer, 34(3): 538–547. 2020.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n  \n \n 1 download\n \n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n\n\n\n
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@article{holloway2020a,\n\ttitle = {Assessment of {Thermochemistry} {Modeling} for {Hypersonic} {Flow} over a {Double} {Cone}},\n\tvolume = {34},\n\tdoi = {10.2514/1.T5792},\n\tabstract = {The influence of different assumptions for thermochemistry modeling in hypersonic flow over a double-cone geometry is investigated. A computational fluid dynamics analysis is used to study the double cone in three different thermochemical cases, nonequilibrium flow, equilibrium flow, and frozen flow, for four different mixtures of nitrogen and oxygen. Specific areas of interest include the thermochemistry model effects on the flowfield and surface properties. The resulting aerodynamic loads are compared with experiments and indicate that thermochemistry modeling assumptions play a significant role in determining surface properties. It is also shown that heat loading is more sensitive to thermochemical modeling than drag and suggests that an accurate measurement of surface heat transfer is of particular interest. Careful analysis also reveals that high-enthalpy and pure oxygen flows are particularly sensitive to the thermochemistry model assumed. Consistent overprediction or underprediction of pressure drag and heat load by all three chemistry models for most of the cases considered indicates a fundamental difference between the actual experiments and the simulations, thus limiting the usefulness of the double-cone data for validation of thermochemistry models.},\n\tnumber = {3},\n\tjournal = {Journal of Thermophysics and Heat Transfer},\n\tauthor = {Holloway, Michael E. and Hanquist, Kyle M. and Boyd, Iain D.},\n\tyear = {2020},\n\tkeywords = {own},\n\tpages = {538--547},\n}\n\n\n\n
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\n The influence of different assumptions for thermochemistry modeling in hypersonic flow over a double-cone geometry is investigated. A computational fluid dynamics analysis is used to study the double cone in three different thermochemical cases, nonequilibrium flow, equilibrium flow, and frozen flow, for four different mixtures of nitrogen and oxygen. Specific areas of interest include the thermochemistry model effects on the flowfield and surface properties. The resulting aerodynamic loads are compared with experiments and indicate that thermochemistry modeling assumptions play a significant role in determining surface properties. It is also shown that heat loading is more sensitive to thermochemical modeling than drag and suggests that an accurate measurement of surface heat transfer is of particular interest. Careful analysis also reveals that high-enthalpy and pure oxygen flows are particularly sensitive to the thermochemistry model assumed. Consistent overprediction or underprediction of pressure drag and heat load by all three chemistry models for most of the cases considered indicates a fundamental difference between the actual experiments and the simulations, thus limiting the usefulness of the double-cone data for validation of thermochemistry models.\n
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\n \n\n \n \n Venturi, S.; Jaffe, R. L.; and Panesi, M.\n\n\n \n \n \n \n \n Bayesian Machine Learning Approach to the Quantification of Uncertainties on Ab Initio Potential Energy Surfaces.\n \n \n \n \n\n\n \n\n\n\n Journal of Physical Chemistry A, 124(25): 5129–5146. June 2020.\n Publisher: American Chemical Society\n\n\n\n
\n\n\n\n \n \n \"BayesianPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{venturi2020,\n\ttitle = {Bayesian {Machine} {Learning} {Approach} to the {Quantification} of {Uncertainties} on {Ab} {Initio} {Potential} {Energy} {Surfaces}},\n\tvolume = {124},\n\turl = {https://pubs.acs.org/doi/full/10.1021/acs.jpca.0c02395},\n\tdoi = {10.1021/ACS.JPCA.0C02395/ASSET/IMAGES/LARGE/JP0C02395_0012.JPEG},\n\tabstract = {This work introduces a novel methodology for the quantification of uncertainties associated with potential energy surfaces (PESs) computed from first-principles quantum mechanical calculations. The methodology relies on Bayesian inference and machine learning techniques to construct a stochastic PES and to express the inadequacies associated with the ab initio data points and their fit. By combining high fidelity calculations and reduced-order modeling, the resulting stochastic surface is efficiently forward propagated via quasi-classical trajectory and master equation calculations. In this way, the PES contribution to the uncertainty on predefined quantities of interest (QoIs) is explicitly determined. This study is done at both microscopic (e.g., rovibrational-specific rate coefficients) and macroscopic (e.g., thermal and chemical relaxation properties) levels. A correlation analysis is finally applied to identify the PES regions that require further refinement, based on their effects on the QoI reliability. The methodology is applied to the study of singlet (11A′) and quintet (25A′) PESs describing the interaction between O2 molecules and O atoms in their ground electronic state. The investigation of the singlet surface reveals a negligible uncertainty on the kinetic properties and relaxation times, which are found to be in excellent agreement with the ones previously published in the literature. On the other hand, the methodology demonstrated significant uncertainty on the quintet surface, due to inaccuracies in the description of the exchange barrier and the repulsive wall. When forward propagated, this uncertainty is responsible for the variability of 1 order of magnitude in the vibrational relaxation time and of factor four in the exchange reaction rate coefficient, both at 2500 K.},\n\tnumber = {25},\n\tjournal = {Journal of Physical Chemistry A},\n\tauthor = {Venturi, S. and Jaffe, R. L. and Panesi, M.},\n\tmonth = jun,\n\tyear = {2020},\n\tnote = {Publisher: American Chemical Society},\n\tpages = {5129--5146},\n}\n\n\n\n
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\n This work introduces a novel methodology for the quantification of uncertainties associated with potential energy surfaces (PESs) computed from first-principles quantum mechanical calculations. The methodology relies on Bayesian inference and machine learning techniques to construct a stochastic PES and to express the inadequacies associated with the ab initio data points and their fit. By combining high fidelity calculations and reduced-order modeling, the resulting stochastic surface is efficiently forward propagated via quasi-classical trajectory and master equation calculations. In this way, the PES contribution to the uncertainty on predefined quantities of interest (QoIs) is explicitly determined. This study is done at both microscopic (e.g., rovibrational-specific rate coefficients) and macroscopic (e.g., thermal and chemical relaxation properties) levels. A correlation analysis is finally applied to identify the PES regions that require further refinement, based on their effects on the QoI reliability. The methodology is applied to the study of singlet (11A′) and quintet (25A′) PESs describing the interaction between O2 molecules and O atoms in their ground electronic state. The investigation of the singlet surface reveals a negligible uncertainty on the kinetic properties and relaxation times, which are found to be in excellent agreement with the ones previously published in the literature. On the other hand, the methodology demonstrated significant uncertainty on the quintet surface, due to inaccuracies in the description of the exchange barrier and the repulsive wall. When forward propagated, this uncertainty is responsible for the variability of 1 order of magnitude in the vibrational relaxation time and of factor four in the exchange reaction rate coefficient, both at 2500 K.\n
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\n \n\n \n \n Gupta, A.; and Argrow, B.\n\n\n \n \n \n \n Analytical Approach for Aero-Optical and Atmospheric Effects in Supersonic Flow Fields.\n \n \n \n\n\n \n\n\n\n In Orlando, FL, January 2020. AIAA 2020-0684\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@inproceedings{gupta2020,\n\taddress = {Orlando, FL},\n\ttitle = {Analytical {Approach} for {Aero}-{Optical} and {Atmospheric} {Effects} in {Supersonic} {Flow} {Fields}},\n\tpublisher = {AIAA 2020-0684},\n\tauthor = {Gupta, Anubhav and Argrow, Brian},\n\tmonth = jan,\n\tyear = {2020},\n}\n\n\n\n
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\n \n\n \n \n Vasile, J. D; Bryson, J. T; Sahu, J.; Paul, J. L; and Gruenwald, B. C\n\n\n \n \n \n \n Aerodynamic Dataset Generation of a Long-Range Projectile.\n \n \n \n\n\n \n\n\n\n Technical Report ARL-TR-9019, 2020.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
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@techreport{vasile2020,\n\taddress = {ARL-TR-9019},\n\ttitle = {Aerodynamic {Dataset} {Generation} of a {Long}-{Range} {Projectile}},\n\tauthor = {Vasile, Joseph D and Bryson, Joshua T and Sahu, Jubaraj and Paul, Justin L and Gruenwald, Benjamin C},\n\tyear = {2020},\n\tkeywords = {ARL-TR-9019, US Army Combat Capabilities Development Command (CCDC) Army Research Laboratory (ARL), aerodynamic characterization, airframe design, computational fluid dynamics, lift-to-drag, long-range guided projectiles},\n}\n\n\n\n
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\n  \n 2019\n \n \n (46)\n \n \n
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\n \n\n \n \n Huang, D.\n\n\n \n \n \n \n \n Development of a Hypersonic Aerothermoelastic Framework and Its Application to Flutter and Aerothermoelastic Scaling of Skin Panels.\n \n \n \n \n\n\n \n\n\n\n Ph.D. Thesis, University of Michigan, Ann Arbor, 2019.\n \n\n\n\n
\n\n\n\n \n \n \"DevelopmentPaper\n  \n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@phdthesis{huang2019a,\n\taddress = {Ann Arbor},\n\ttitle = {Development of a {Hypersonic} {Aerothermoelastic} {Framework} and {Its} {Application} to {Flutter} and {Aerothermoelastic} {Scaling} of {Skin} {Panels}},\n\turl = {https://hdl.handle.net/2027.42/151461},\n\tschool = {University of Michigan},\n\tauthor = {Huang, Daning},\n\tyear = {2019},\n}\n\n\n\n
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\n \n\n \n \n Ratnayake, N.; Krist, S.; Ghaffari, F.; and Deere, K.\n\n\n \n \n \n \n Computational Fluid Dynamics Methods used in the Development of the Space Launch System Liftoff and Transition Lineloads Databases.\n \n \n \n\n\n \n\n\n\n In Dallas, Texas, June 2019. AIAA\n \n\n\n\n
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@inproceedings{ratnayake2019,\n\taddress = {Dallas, Texas},\n\ttitle = {Computational {Fluid} {Dynamics} {Methods} used in the {Development} of the {Space} {Launch} {System} {Liftoff} and {Transition} {Lineloads} {Databases}},\n\tpublisher = {AIAA},\n\tauthor = {Ratnayake, Nalin and Krist, Steven and Ghaffari, Farhad and Deere, Karen},\n\tmonth = jun,\n\tyear = {2019},\n}\n\n\n\n
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\n \n\n \n \n Chaudhry, R. S; and Candler, G. V\n\n\n \n \n \n \n Statistical Analyses of Quasiclassical Trajectory Data for Air Dissociation.\n \n \n \n\n\n \n\n\n\n In San Diego, CA, January 2019. AIAA Paper 2019-0789\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@inproceedings{chaudhry2019,\n\taddress = {San Diego, CA},\n\ttitle = {Statistical {Analyses} of {Quasiclassical} {Trajectory} {Data} for {Air} {Dissociation}},\n\tdoi = {10.2514/6.2019-0789},\n\tpublisher = {AIAA Paper 2019-0789},\n\tauthor = {Chaudhry, Ross S and Candler, Graham V},\n\tmonth = jan,\n\tyear = {2019},\n}\n\n\n\n
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\n \n\n \n \n Mortari, D.; Johnston, H.; and Smith, L.\n\n\n \n \n \n \n \n High accuracy least-squares solutions of nonlinear differential equations.\n \n \n \n \n\n\n \n\n\n\n Journal of Computational and Applied Mathematics, 352: 293–307. May 2019.\n \n\n\n\n
\n\n\n\n \n \n \"HighPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{mortari2019,\n\ttitle = {High accuracy least-squares solutions of nonlinear differential equations},\n\tvolume = {352},\n\tissn = {0377-0427},\n\turl = {https://www.sciencedirect.com/science/article/pii/S0377042718307325},\n\tdoi = {10.1016/j.cam.2018.12.007},\n\tabstract = {This study shows how to obtain least-squares solutions to initial and boundary value problems of ordinary nonlinear differential equations. The proposed method begins using an approximate solution obtained by any existing integrator. Then, a least-squares fitting of this approximate solution is obtained using a constrained expression, derived from Theory of Connections. In this expression, the differential equation constraints are embedded and are always satisfied. The resulting constrained expression is then used as an initial guess in a Newton iterative process that increases the solution accuracy to machine error level in no more than two iterations for most of the problems considered. An analysis of speed and accuracy has been conducted for this method using two nonlinear differential equations. For non-smooth solutions or for long integration times, a piecewise approach is proposed. The highly accurate value estimated at the final time is then used as the new initial guess for the next time range, and this process is repeated for subsequent time ranges. This approach has been applied and validated solving the Duffing oscillator obtaining a final solution error on the order of 10−12. To complete the study, a final numerical test is provided for a boundary value problem with a known solution.},\n\turldate = {2024-04-24},\n\tjournal = {Journal of Computational and Applied Mathematics},\n\tauthor = {Mortari, Daniele and Johnston, Hunter and Smith, Lidia},\n\tmonth = may,\n\tyear = {2019},\n\tkeywords = {Embedded linear constraints, Interpolation, Linear least-squares},\n\tpages = {293--307},\n}\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n
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\n This study shows how to obtain least-squares solutions to initial and boundary value problems of ordinary nonlinear differential equations. The proposed method begins using an approximate solution obtained by any existing integrator. Then, a least-squares fitting of this approximate solution is obtained using a constrained expression, derived from Theory of Connections. In this expression, the differential equation constraints are embedded and are always satisfied. The resulting constrained expression is then used as an initial guess in a Newton iterative process that increases the solution accuracy to machine error level in no more than two iterations for most of the problems considered. An analysis of speed and accuracy has been conducted for this method using two nonlinear differential equations. For non-smooth solutions or for long integration times, a piecewise approach is proposed. The highly accurate value estimated at the final time is then used as the new initial guess for the next time range, and this process is repeated for subsequent time ranges. This approach has been applied and validated solving the Duffing oscillator obtaining a final solution error on the order of 10−12. To complete the study, a final numerical test is provided for a boundary value problem with a known solution.\n
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\n \n\n \n \n Linke, J.; Du, J.; Loewenhoff, T.; Pintsuk, G.; Spilker, B.; Steudel, I.; and Wirtz, M.\n\n\n \n \n \n \n Challenges for plasma-facing components in nuclear fusion.\n \n \n \n\n\n \n\n\n\n Matter and Radiation at Extremes, 4(5): 056201. August 2019.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{linke2019,\n\ttitle = {Challenges for plasma-facing components in nuclear fusion},\n\tvolume = {4},\n\tissn = {2468-2047},\n\tdoi = {10.1063/1.5090100},\n\tabstract = {The interaction processes between the burning plasma and the first wall in a fusion reactor are diverse: the first wall will be exposed to extreme thermal loads of up to several tens of megawatts per square meter during quasistationary operation, combined with repeated intense thermal shocks (with energy densities of up to several megajoules per square meter and pulse durations on a millisecond time scale). In addition to these thermal loads, the wall will be subjected to bombardment by plasma ions and neutral particles (D, T, and He) and by energetic neutrons with energies up to 14 MeV. Hopefully, ITER will not only demonstrate that thermonuclear fusion of deuterium and tritium is feasible in magnetic confinement regimes; it will also act as a first test device for plasma-facing materials (PFMs) and plasma-facing components (PFCs) under realistic synergistic loading scenarios that cover all the above-mentioned load types. In the absence of an integrated test device, material tests are being performed primarily in specialized facilities that concentrate only on the most essential material properties. New multipurpose test facilities are now available that can also focus on more complex loading scenarios and thus help to minimize the risk of an unexpected material or component failure. Thermonuclear fusion—both with magnetic and with inertial confinement—is making great progress, and the goal of scientific break-even will be reached soon. However, to achieve that end, significant technical problems, particularly in the field of high-temperature and radiation-resistant materials, must be solved. With ITER, the first nuclear reactor that burns a deuterium–tritium plasma with a fusion power gain Q ≥ 10 will start operation in the next decade. To guarantee safe operation of this rather sophisticated fusion device, new PFMs and PFCs that are qualified to withstand the harsh environments in such a tokamak reactor have been developed and are now entering the manufacturing stage.},\n\tnumber = {5},\n\turldate = {2024-04-24},\n\tjournal = {Matter and Radiation at Extremes},\n\tauthor = {Linke, Jochen and Du, Juan and Loewenhoff, Thorsten and Pintsuk, Gerald and Spilker, Benjamin and Steudel, Isabel and Wirtz, Marius},\n\tmonth = aug,\n\tyear = {2019},\n\tpages = {056201},\n}\n\n\n\n\n\n\n\n
\n
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\n The interaction processes between the burning plasma and the first wall in a fusion reactor are diverse: the first wall will be exposed to extreme thermal loads of up to several tens of megawatts per square meter during quasistationary operation, combined with repeated intense thermal shocks (with energy densities of up to several megajoules per square meter and pulse durations on a millisecond time scale). In addition to these thermal loads, the wall will be subjected to bombardment by plasma ions and neutral particles (D, T, and He) and by energetic neutrons with energies up to 14 MeV. Hopefully, ITER will not only demonstrate that thermonuclear fusion of deuterium and tritium is feasible in magnetic confinement regimes; it will also act as a first test device for plasma-facing materials (PFMs) and plasma-facing components (PFCs) under realistic synergistic loading scenarios that cover all the above-mentioned load types. In the absence of an integrated test device, material tests are being performed primarily in specialized facilities that concentrate only on the most essential material properties. New multipurpose test facilities are now available that can also focus on more complex loading scenarios and thus help to minimize the risk of an unexpected material or component failure. Thermonuclear fusion—both with magnetic and with inertial confinement—is making great progress, and the goal of scientific break-even will be reached soon. However, to achieve that end, significant technical problems, particularly in the field of high-temperature and radiation-resistant materials, must be solved. With ITER, the first nuclear reactor that burns a deuterium–tritium plasma with a fusion power gain Q ≥ 10 will start operation in the next decade. To guarantee safe operation of this rather sophisticated fusion device, new PFMs and PFCs that are qualified to withstand the harsh environments in such a tokamak reactor have been developed and are now entering the manufacturing stage.\n
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\n \n\n \n \n He, R.; Ding, G.; Zhang, K.; Li, Y.; and Fang, D.\n\n\n \n \n \n \n Fabrication of SiC ceramic architectures using stereolithography combined with precursor infiltration and pyrolysis.\n \n \n \n\n\n \n\n\n\n Ceramics International, 45(11): 14006–14014. August 2019.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{he_fabrication_2019,\n\ttitle = {Fabrication of {SiC} ceramic architectures using stereolithography combined with precursor infiltration and pyrolysis},\n\tvolume = {45},\n\tissn = {0272-8842},\n\tdoi = {10.1016/j.ceramint.2019.04.100},\n\tabstract = {Stereolithography based additive manufacturing provides a new route to produce ceramic architectures with complex geometries. In this study, 3D structured SiC ceramic architectures were fabricated by stereolithography based additive manufacturing combined with precursor infiltration and pyrolysis (PIP). Firstly, photosensitive SiC slurry was prepared. Then, stereolithography was conducted to fabricate complex-shaped green SiC parts. Polymer burn-out was subsequently performed, and porous SiC preforms were produced. After that, precursor infiltration and pyrolysis was used to improve the density and strength. Finally, 3D-structured SiC ceramic architectures with high accuracy and quality were obtained. It is believed that this study can give some fundamental understanding for the additive manufacturing of SiC ceramic structures.},\n\tnumber = {11},\n\turldate = {2023-10-28},\n\tjournal = {Ceramics International},\n\tauthor = {He, Rujie and Ding, Guojiao and Zhang, Keqiang and Li, Ying and Fang, Daining},\n\tmonth = aug,\n\tyear = {2019},\n\tkeywords = {Additive manufacturing, Precursor infiltration and pyrolysis, Silicon carbide, Stereolithography},\n\tpages = {14006--14014},\n}\n\n\n\n\n\n\n\n
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\n Stereolithography based additive manufacturing provides a new route to produce ceramic architectures with complex geometries. In this study, 3D structured SiC ceramic architectures were fabricated by stereolithography based additive manufacturing combined with precursor infiltration and pyrolysis (PIP). Firstly, photosensitive SiC slurry was prepared. Then, stereolithography was conducted to fabricate complex-shaped green SiC parts. Polymer burn-out was subsequently performed, and porous SiC preforms were produced. After that, precursor infiltration and pyrolysis was used to improve the density and strength. Finally, 3D-structured SiC ceramic architectures with high accuracy and quality were obtained. It is believed that this study can give some fundamental understanding for the additive manufacturing of SiC ceramic structures.\n
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\n \n\n \n \n Sullivan, B. T.; Whalen, T. J.; Laurence, S. J.; and Bodony, D. J.\n\n\n \n \n \n \n Direct Simulation of Fluid-Structure Interaction in Compression Ramp with Embedded Compliant Panel.\n \n \n \n\n\n \n\n\n\n In AIAA Aviation 2019 Forum, Dallas, Texas, June 2019. AIAA Paper 2019-3545\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{sullivan2019,\n\taddress = {Dallas, Texas},\n\ttitle = {Direct {Simulation} of {Fluid}-{Structure} {Interaction} in {Compression} {Ramp} with {Embedded} {Compliant} {Panel}},\n\tisbn = {978-1-62410-589-0},\n\tdoi = {10.2514/6.2019-3545},\n\tlanguage = {en},\n\turldate = {2023-08-09},\n\tbooktitle = {{AIAA} {Aviation} 2019 {Forum}},\n\tpublisher = {AIAA Paper 2019-3545},\n\tauthor = {Sullivan, Bryson T. and Whalen, Thomas J. and Laurence, Stuart J. and Bodony, Daniel J.},\n\tmonth = jun,\n\tyear = {2019},\n}\n\n\n\n\n\n\n\n
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\n \n\n \n \n Casper, K. M.; Beresh, S. J.; Henfling, J. F.; Spillers, R. W.; Hunter, P.; and Spitzer, S.\n\n\n \n \n \n \n Hypersonic Fluid–Structure Interactions Due to Intermittent Turbulent Spots on a Slender Cone.\n \n \n \n\n\n \n\n\n\n AIAA Journal, 57(2): 749–759. 2019.\n Publisher: American Institute of Aeronautics and Astronautics _eprint: https://doi.org/10.2514/1.J057374\n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@article{casper2019,\n\ttitle = {Hypersonic {Fluid}–{Structure} {Interactions} {Due} to {Intermittent} {Turbulent} {Spots} on a {Slender} {Cone}},\n\tvolume = {57},\n\tissn = {0001-1452},\n\tdoi = {10.2514/1.J057374},\n\tabstract = {Fluid–structure interactions due to intermittent turbulent spots were studied on a 7 deg half-angle cone in the Sandia Hypersonic Wind Tunnel at Mach 5 and 8 and in the Purdue Boeing/U.S. Air Force Office of Scientific Research Mach 6 Quiet Tunnel. A thin composite panel was integrated into the cone and the response to boundary-layer disturbances was characterized by accelerometers on the backside of the panel. Under quiet flow conditions at Mach 6, the cone boundary layer remained laminar. Artificially generated turbulent spots excited a directionally dependent panel response. When the spot generation frequency matched a structural natural frequency of the panel, resonance would occur, and responses over 200 times greater than under a laminar boundary layer were obtained. At Mach 5 and 8 under noisy flow conditions, natural transition driven by the wind-tunnel acoustic noise dominated the panel response. A single turbulent spot could not change this forced response. However, at higher spot burst rates, an elevated vibrational response was observed during transition at frequencies corresponding to the distribution of turbulent spots in the transitional flow. Once turbulent flow developed, the structural response dropped because the intermittent forcing from the spots no longer drove panel vibration.},\n\tnumber = {2},\n\turldate = {2023-08-03},\n\tjournal = {AIAA Journal},\n\tauthor = {Casper, Katya M. and Beresh, Steven J. and Henfling, John F. and Spillers, Russell W. and Hunter, Patrick and Spitzer, Seth},\n\tyear = {2019},\n\tnote = {Publisher: American Institute of Aeronautics and Astronautics\n\\_eprint: https://doi.org/10.2514/1.J057374},\n\tpages = {749--759},\n}\n\n\n\n\n\n\n\n\n\n\n\n
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\n Fluid–structure interactions due to intermittent turbulent spots were studied on a 7 deg half-angle cone in the Sandia Hypersonic Wind Tunnel at Mach 5 and 8 and in the Purdue Boeing/U.S. Air Force Office of Scientific Research Mach 6 Quiet Tunnel. A thin composite panel was integrated into the cone and the response to boundary-layer disturbances was characterized by accelerometers on the backside of the panel. Under quiet flow conditions at Mach 6, the cone boundary layer remained laminar. Artificially generated turbulent spots excited a directionally dependent panel response. When the spot generation frequency matched a structural natural frequency of the panel, resonance would occur, and responses over 200 times greater than under a laminar boundary layer were obtained. At Mach 5 and 8 under noisy flow conditions, natural transition driven by the wind-tunnel acoustic noise dominated the panel response. A single turbulent spot could not change this forced response. However, at higher spot burst rates, an elevated vibrational response was observed during transition at frequencies corresponding to the distribution of turbulent spots in the transitional flow. Once turbulent flow developed, the structural response dropped because the intermittent forcing from the spots no longer drove panel vibration.\n
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\n \n\n \n \n Currao, G. M. D.; Neely, A. J.; Kennell, C. M.; Gai, S. L.; and Buttsworth, D. R.\n\n\n \n \n \n \n Hypersonic Fluid–Structure Interaction on a Cantilevered Plate with Shock Impingement.\n \n \n \n\n\n \n\n\n\n AIAA Journal, 57(11): 4819–4834. 2019.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{currao2019,\n\ttitle = {Hypersonic {Fluid}–{Structure} {Interaction} on a {Cantilevered} {Plate} with {Shock} {Impingement}},\n\tvolume = {57},\n\tissn = {0001-1452},\n\tdoi = {10.2514/1.J058375},\n\tabstract = {This work is focused on a hypersonic aeroelastic experiment involving a shock impinging on compliant cantilevered plate at Mach 5.8. The shock induces a pressure differential across the plate thickness that drives its oscillatory behavior. Transition takes place within the separated region, resulting in a fully turbulent boundary layer at the reattachment point, in agreement with previous relevant work. A schlieren system and pressure-sensitive paint are used to measure structural displacement and pressure distribution, respectively. For small deflections, transition results in peak pressure values 15\\% greater than twoway predictions based on unsteady Reynolds-averaged Navier–Stokes (RANS) equations. Peak pressure evolution is predicted with the piston theory with good accuracy. The reference enthalpy method is corrected on the basis of the Reynolds-averaged Navier–Stokes solution, and it is used to estimate the heat-flux distribution downstream of the reattachment point. Görtler-like vortices are observed and measured in the reattachment region, and their magnitude is affected by the plate deflection. Large trailing-edge displacements result in a smaller streamline curvature at the reattachment point and, consequently, in smaller vortices. Finally, the data are used to predict the performance of two-dimensional control surfaces using the conceptual equivalence of oblique shock-wave/boundary-layer interaction and compression corners. This work aims to establish the accuracy of RANS simulations and low-fidelity models in the reconstruction of the peak heating and peak pressure evolution to bridge ground-testing and real-flight conditions in terms of flap-efficiency predictions and to design an experiment that can be simulated using computationally inexpensive two-dimensional solvers.},\n\tnumber = {11},\n\turldate = {2023-08-03},\n\tjournal = {AIAA Journal},\n\tauthor = {Currao, Gaetano M. D. and Neely, Andrew J. and Kennell, Christopher M. and Gai, Sudhir L. and Buttsworth, David R.},\n\tyear = {2019},\n\tpages = {4819--4834},\n}\n\n\n\n\n\n\n\n\n\n\n\n
\n
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\n This work is focused on a hypersonic aeroelastic experiment involving a shock impinging on compliant cantilevered plate at Mach 5.8. The shock induces a pressure differential across the plate thickness that drives its oscillatory behavior. Transition takes place within the separated region, resulting in a fully turbulent boundary layer at the reattachment point, in agreement with previous relevant work. A schlieren system and pressure-sensitive paint are used to measure structural displacement and pressure distribution, respectively. For small deflections, transition results in peak pressure values 15% greater than twoway predictions based on unsteady Reynolds-averaged Navier–Stokes (RANS) equations. Peak pressure evolution is predicted with the piston theory with good accuracy. The reference enthalpy method is corrected on the basis of the Reynolds-averaged Navier–Stokes solution, and it is used to estimate the heat-flux distribution downstream of the reattachment point. Görtler-like vortices are observed and measured in the reattachment region, and their magnitude is affected by the plate deflection. Large trailing-edge displacements result in a smaller streamline curvature at the reattachment point and, consequently, in smaller vortices. Finally, the data are used to predict the performance of two-dimensional control surfaces using the conceptual equivalence of oblique shock-wave/boundary-layer interaction and compression corners. This work aims to establish the accuracy of RANS simulations and low-fidelity models in the reconstruction of the peak heating and peak pressure evolution to bridge ground-testing and real-flight conditions in terms of flap-efficiency predictions and to design an experiment that can be simulated using computationally inexpensive two-dimensional solvers.\n
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\n \n\n \n \n Huang, D.; Friedmann, P. P.; and Rokita, T.\n\n\n \n \n \n \n Aerothermoelastic Scaling Laws for Hypersonic Skin Panel Configurations with Arbitrary Flow Orientation.\n \n \n \n\n\n \n\n\n\n AIAA Journal, 57(10): 4377–4392. 2019.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{huang2019,\n\ttitle = {Aerothermoelastic {Scaling} {Laws} for {Hypersonic} {Skin} {Panel} {Configurations} with {Arbitrary} {Flow} {Orientation}},\n\tvolume = {57},\n\tissn = {0001-1452},\n\tdoi = {10.2514/1.J057499},\n\tabstract = {This study describes the development of an efficient aerothermoelastic computational framework and its application to the aerothermoelastic scaling law development. In the framework, a novel approach is developed for the reduced-order model of the fluid solver, which accounts for nonuniform temperature distribution and geometrical scales using simple analytical pointwise models. Subsequently, a new, two-pronged approach to aerothermoelastic scaling is presented. It combines the classical scaling approach with augmentation from numerical simulations of the specific problem. This enables one to obtain useful scaling information for important quantities that cannot be treated by the classical approach. Finally, the framework is applied to study the effect of flow orientation angle on panel flutter and the development of a scaling law for a hypersonic skin panel configuration.},\n\tnumber = {10},\n\turldate = {2023-08-03},\n\tjournal = {AIAA Journal},\n\tauthor = {Huang, Daning and Friedmann, Peretz P. and Rokita, Tomer},\n\tyear = {2019},\n\tpages = {4377--4392},\n}\n\n\n\n\n\n\n\n\n\n\n\n
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\n This study describes the development of an efficient aerothermoelastic computational framework and its application to the aerothermoelastic scaling law development. In the framework, a novel approach is developed for the reduced-order model of the fluid solver, which accounts for nonuniform temperature distribution and geometrical scales using simple analytical pointwise models. Subsequently, a new, two-pronged approach to aerothermoelastic scaling is presented. It combines the classical scaling approach with augmentation from numerical simulations of the specific problem. This enables one to obtain useful scaling information for important quantities that cannot be treated by the classical approach. Finally, the framework is applied to study the effect of flow orientation angle on panel flutter and the development of a scaling law for a hypersonic skin panel configuration.\n
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\n \n\n \n \n Mullen, C. D.; Moyes, A.; Kocian, T. S.; and Reed, H. L.\n\n\n \n \n \n \n Heat Transfer and Boundary-Layer Stability Analysis of Subscale BOLT and the Fin Cone.\n \n \n \n\n\n \n\n\n\n In AIAA Aviation 2019 Forum, Dallas, Texas, June 2019. American Institute of Aeronautics and Astronautics\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@inproceedings{mullen2019,\n\taddress = {Dallas, Texas},\n\ttitle = {Heat {Transfer} and {Boundary}-{Layer} {Stability} {Analysis} of {Subscale} {BOLT} and the {Fin} {Cone}},\n\tisbn = {978-1-62410-589-0},\n\tdoi = {10.2514/6.2019-3081},\n\tlanguage = {en},\n\turldate = {2023-06-22},\n\tbooktitle = {{AIAA} {Aviation} 2019 {Forum}},\n\tpublisher = {American Institute of Aeronautics and Astronautics},\n\tauthor = {Mullen, Charles D. and Moyes, Alexander and Kocian, Travis S. and Reed, Helen L.},\n\tmonth = jun,\n\tyear = {2019},\n}\n\n\n\n\n\n\n\n\n\n\n\n
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\n \n\n \n \n Grover, M. S.; Schwartzentruber, T. E.; Varga, Z.; and Truhlar, D. G.\n\n\n \n \n \n \n \n Vibrational energy transfer and collision-induced dissociation in O + O2 collisions.\n \n \n \n \n\n\n \n\n\n\n Journal of Thermophysics and Heat Transfer, 33(3): 797–807. February 2019.\n Publisher: American Institute of Aeronautics and Astronautics Inc.\n\n\n\n
\n\n\n\n \n \n \"VibrationalPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
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@article{grover2019a,\n\ttitle = {Vibrational energy transfer and collision-induced dissociation in {O} + {O2} collisions},\n\tvolume = {33},\n\turl = {https://arc.aiaa.org/doi/10.2514/1.T5551},\n\tdoi = {10.2514/1.T5551/ASSET/IMAGES/LARGE/FIGURE12.JPEG},\n\tabstract = {This paper presents molecular dynamics calculations of vibrational energy transfer and nonequilibrium dissociation in O2 + O collisions. The O2 + O interactions are modeled using nine potential energy surfaces corresponding to the 11A', 21A', 11A' 0, 13A', 23A', 13A", 15A', 25A', and 15A" states, which govern electronically adiabatic collisions of ground-electronic-state collisions of diatomic oxygen with atomic oxygen. Characteristic vibrational excitation times are calculated over a temperature range of T = 3000 K to T = 15,000 K, and nonequilibrium dissociation rate coefficients are calculated over a temperature range of T = 6000 K to T = 15,000 K. Vibrational relaxation rates, specific to each PES, are found to vary by over an order of magnitude, indicating that all spin couplings and spatial degeneracies must be considered for accurate predictions of O2 + O collisions. It has been observed that the characteristic vibrational excitation time for O2 + O interactions is weakly dependent on temperature and increases slightly with increasing temperature. Predicted nonequilibrium dissociation rates, during quasi-steady state. Agree well with available experimental data, and the coupling between vibrational energy and dissociation is characterized.},\n\tnumber = {3},\n\tjournal = {Journal of Thermophysics and Heat Transfer},\n\tauthor = {Grover, Maninder S. and Schwartzentruber, Thomas E. and Varga, Zoltan and Truhlar, Donald G.},\n\tmonth = feb,\n\tyear = {2019},\n\tnote = {Publisher: American Institute of Aeronautics and Astronautics Inc.},\n\tkeywords = {Born Oppenheimer Approximation, CFD, Collision Induced Dissociation, Direct Simulation Monte Carlo, Energy Distribution, Flight Testing, Hypersonic Flight, Lennard Jones Potential, Molecular Dynamics, Quasi Steady States},\n\tpages = {797--807},\n}\n\n\n\n
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\n This paper presents molecular dynamics calculations of vibrational energy transfer and nonequilibrium dissociation in O2 + O collisions. The O2 + O interactions are modeled using nine potential energy surfaces corresponding to the 11A', 21A', 11A' 0, 13A', 23A', 13A\", 15A', 25A', and 15A\" states, which govern electronically adiabatic collisions of ground-electronic-state collisions of diatomic oxygen with atomic oxygen. Characteristic vibrational excitation times are calculated over a temperature range of T = 3000 K to T = 15,000 K, and nonequilibrium dissociation rate coefficients are calculated over a temperature range of T = 6000 K to T = 15,000 K. Vibrational relaxation rates, specific to each PES, are found to vary by over an order of magnitude, indicating that all spin couplings and spatial degeneracies must be considered for accurate predictions of O2 + O collisions. It has been observed that the characteristic vibrational excitation time for O2 + O interactions is weakly dependent on temperature and increases slightly with increasing temperature. Predicted nonequilibrium dissociation rates, during quasi-steady state. Agree well with available experimental data, and the coupling between vibrational energy and dissociation is characterized.\n
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\n \n\n \n \n Hara, K.; and Hanquist, K. M.\n\n\n \n \n \n \n Verification Test Cases of Grid-Based Direct Kinetic Modeling Framework for Plasma Flows.\n \n \n \n\n\n \n\n\n\n 2019.\n \n\n\n\n
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@misc{hara2019,\n\taddress = {SIAM Conference on Computational Science and Engineering},\n\ttype = {Conference {Presentation}},\n\ttitle = {Verification {Test} {Cases} of {Grid}-{Based} {Direct} {Kinetic} {Modeling} {Framework} for {Plasma} {Flows}},\n\tauthor = {Hara, Kentaro and Hanquist, Kyle M.},\n\tyear = {2019},\n\tkeywords = {own, presentation},\n}\n\n\n\n
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\n \n\n \n \n Bezverkhnii, N. O.; Bobashev, S. V.; Kolychev, A. V.; Monakhov, N. A.; Ponyaev, S. A.; and Sakharov, V. A.\n\n\n \n \n \n \n \n Study of the Effect of Electron Cooling: Overview of the Current State.\n \n \n \n \n\n\n \n\n\n\n Technical Physics 2019 64:3, 64(3): 287–292. May 2019.\n Publisher: Springer\n\n\n\n
\n\n\n\n \n \n \"StudyPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n\n\n\n
\n 
@article{bezverkhnii2019,\n\ttitle = {Study of the {Effect} of {Electron} {Cooling}: {Overview} of the {Current} {State}},\n\tvolume = {64},\n\turl = {https://link.springer.com/article/10.1134/S106378421903006X},\n\tdoi = {10.1134/S106378421903006X},\n\tabstract = {Investigation results of the effect of electron cooling are considered. The current state-of-the-art is analyzed. The possibilities are discussed for the experimental study of the electron cooling phenomenon using a large shock tube and plasma-gas-dynamic stand at the Ioffe Institute.},\n\tnumber = {3},\n\tjournal = {Technical Physics 2019 64:3},\n\tauthor = {Bezverkhnii, N. O. and Bobashev, S. V. and Kolychev, A. V. and Monakhov, N. A. and Ponyaev, S. A. and Sakharov, V. A.},\n\tmonth = may,\n\tyear = {2019},\n\tnote = {Publisher: Springer},\n\tkeywords = {Classical and Continuum Physics},\n\tpages = {287--292},\n}\n\n\n\n
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\n Investigation results of the effect of electron cooling are considered. The current state-of-the-art is analyzed. The possibilities are discussed for the experimental study of the electron cooling phenomenon using a large shock tube and plasma-gas-dynamic stand at the Ioffe Institute.\n
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\n \n\n \n \n de Brey, C.; Musu, L.; McFarland, J.; Wilkinson-Flicker, S.; Diliberti, M.; Zhang, A.; Branstetter, C.; and Wang, X.\n\n\n \n \n \n \n Status and Trends in the Education of Racial and Ethnic Groups 2018.\n \n \n \n\n\n \n\n\n\n Technical Report 2019.\n Issue: NCES 2019-038\n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@techreport{debrey2019,\n\ttitle = {Status and {Trends} in the {Education} of {Racial} and {Ethnic} {Groups} 2018},\n\tauthor = {de Brey, Cristobal and Musu, Lauren and McFarland, Joel and Wilkinson-Flicker, Sidney and Diliberti, Melissa and Zhang, Anlan and Branstetter, Claire and Wang, Xiaolei},\n\tyear = {2019},\n\tnote = {Issue: NCES 2019-038},\n}\n\n\n\n
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\n \n\n \n \n Wu, Y; Limbach, C M; Tropina, A A; and Miles, R B\n\n\n \n \n \n \n Space and time analysis of \\N\\\\textsubscript\\2\\ vibrational nonequilibrium in the \\N\\\\textsubscript\\2\\ and air nanosecond discharge afterglow.\n \n \n \n\n\n \n\n\n\n In 2019. \n \n\n\n\n
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@inproceedings{wu2019,\n\ttitle = {Space and time analysis of \\{{N}\\}{\\textbackslash}textsubscript\\{2\\} vibrational nonequilibrium in the \\{{N}\\}{\\textbackslash}textsubscript\\{2\\} and air nanosecond discharge afterglow},\n\tauthor = {Wu, Y and Limbach, C M and Tropina, A A and Miles, R B},\n\tyear = {2019},\n}\n\n\n\n
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\n \n\n \n \n Eyi, S.; Hanquist, K. M.; and Boyd, I. D.\n\n\n \n \n \n \n Shape Optimization of Reentry Vehicles to Minimize Heat Loading.\n \n \n \n\n\n \n\n\n\n Journal of Thermophysics and Heat Transfer, 33(3): 785–796. 2019.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n  \n \n 5 downloads\n \n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n\n\n\n
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@article{eyi2019d,\n\ttitle = {Shape {Optimization} of {Reentry} {Vehicles} to {Minimize} {Heat} {Loading}},\n\tvolume = {33},\n\tdoi = {10.2514/1.T5705},\n\tabstract = {The objective of the current study is to designanoptimumreentry vehicle shape thatminimizes heat loading subject to constraints on themaximumvalues of surface heat flux and temperature. A new heat loading formulation is developed for objective function evaluations. Axisymmetric Navier-Stokes and finite-rate chemical reaction equations are solved to evaluate the objectiveandconstraint functions.TheMenterSSTturbulencemodel isemployedfor turbulence closure. A gradient-based method is used for optimization. The sensitivities of the objective and constraint functions are evaluated using the finite-difference method. In shape optimization, the geometry change or the geometry itself is parameterized using different numbers of nonuniform rational basis spline (NURBS) or Bezier curves. Designs are performed at different trajectory points of the IRV-2 vehicle. The effects of flight path angle and reentry velocity on the heat transfer and trajectory characteristics of the original and designed geometries are quantified.},\n\tnumber = {3},\n\tjournal = {Journal of Thermophysics and Heat Transfer},\n\tauthor = {Eyi, Sinan and Hanquist, Kyle M. and Boyd, Iain D.},\n\tyear = {2019},\n\tkeywords = {own},\n\tpages = {785--796},\n}\n\n\n\n
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\n The objective of the current study is to designanoptimumreentry vehicle shape thatminimizes heat loading subject to constraints on themaximumvalues of surface heat flux and temperature. A new heat loading formulation is developed for objective function evaluations. Axisymmetric Navier-Stokes and finite-rate chemical reaction equations are solved to evaluate the objectiveandconstraint functions.TheMenterSSTturbulencemodel isemployedfor turbulence closure. A gradient-based method is used for optimization. The sensitivities of the objective and constraint functions are evaluated using the finite-difference method. In shape optimization, the geometry change or the geometry itself is parameterized using different numbers of nonuniform rational basis spline (NURBS) or Bezier curves. Designs are performed at different trajectory points of the IRV-2 vehicle. The effects of flight path angle and reentry velocity on the heat transfer and trajectory characteristics of the original and designed geometries are quantified.\n
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\n \n\n \n \n Eyi, S.; Hanquist, K. M.; and Boyd, I. D.\n\n\n \n \n \n \n Shape Optimization of Reentry Vehicles to Minimize Heat Loading.\n \n \n \n\n\n \n\n\n\n In AIAA Science and Technology Forum and Exposition, 2019. AIAA Paper 2019-0973\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n  \n \n 5 downloads\n \n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n\n\n\n
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@inproceedings{eyi2019e,\n\ttitle = {Shape {Optimization} of {Reentry} {Vehicles} to {Minimize} {Heat} {Loading}},\n\tdoi = {10.2514/6.2019-0973},\n\tabstract = {The objective of the current study is to design an optimum reentry vehicle shape that minimizes heat loading subject to constraints on the maximum values of surface heat flux and temperature. A new formulation is developed for the heat loading calculations. Axisymmetric Navier-Stokes and finite rate chemical reaction equations are solved to evaluate the objective and constraint functions. The Menter SST turbulence model is employed for turbulence closure. A gradient-based method is utilized for optimization. The sensitivities of the objective and constraint functions are evaluated using the finite difference method. In design optimization, the geometry change or the geometry itself is parameterized using different numbers of NURBS or Bezier curves. Designs are performed at different trajectory points of the IRV-2 vehicle. The effects of flight path angle and reentry velocity on the heat transfer and trajectory characteristics of the original and designed geometries are quantified.},\n\tbooktitle = {{AIAA} {Science} and {Technology} {Forum} and {Exposition}},\n\tpublisher = {AIAA Paper 2019-0973},\n\tauthor = {Eyi, Sinan and Hanquist, Kyle M. and Boyd, Iain D.},\n\tyear = {2019},\n\tkeywords = {own},\n}\n\n\n\n
\n
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\n The objective of the current study is to design an optimum reentry vehicle shape that minimizes heat loading subject to constraints on the maximum values of surface heat flux and temperature. A new formulation is developed for the heat loading calculations. Axisymmetric Navier-Stokes and finite rate chemical reaction equations are solved to evaluate the objective and constraint functions. The Menter SST turbulence model is employed for turbulence closure. A gradient-based method is utilized for optimization. The sensitivities of the objective and constraint functions are evaluated using the finite difference method. In design optimization, the geometry change or the geometry itself is parameterized using different numbers of NURBS or Bezier curves. Designs are performed at different trajectory points of the IRV-2 vehicle. The effects of flight path angle and reentry velocity on the heat transfer and trajectory characteristics of the original and designed geometries are quantified.\n
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\n \n\n \n \n Dwivedi, A.; Sidharth, G. S.; Nichols, J. W.; Candler, G. V.; and Jovanović, M. R.\n\n\n \n \n \n \n Reattachment streaks in hypersonic compression ramp flow: an input–output analysis.\n \n \n \n\n\n \n\n\n\n Journal of Fluid Mechanics, 880: 113–135. 2019.\n Publisher: Cambridge University Press\n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{dwivedi2019,\n\ttitle = {Reattachment streaks in hypersonic compression ramp flow: an input–output analysis},\n\tvolume = {880},\n\tdoi = {10.1017/JFM.2019.702},\n\tabstract = {We employ global input–output analysis to quantify amplification of exogenous disturbances in compressible boundary layer flows. Using the spatial structure of the dominant response to time-periodic inputs, we explain the origin of steady reattachment streaks in a hypersonic flow over a compression ramp. Our analysis of the laminar shock–boundary layer interaction reveals that the streaks arise from a preferential amplification of upstream counter-rotating vortical perturbations with a specific spanwise wavelength. These streaks are associated with heat-flux striations at the wall near flow reattachment and they can trigger transition to turbulence. The streak wavelength predicted by our analysis compares favourably with observations from two different hypersonic compression ramp experiments. Furthermore, our analysis of inviscid transport equations demonstrates that base-flow deceleration contributes to the amplification of streamwise velocity and that the baroclinic effects are responsible for the production of streamwise vorticity. Finally, the appearance of the temperature streaks near reattachment is triggered by the growth of streamwise velocity and streamwise vorticity perturbations as well as by the amplification of upstream temperature perturbations by the reattachment shock.},\n\tjournal = {Journal of Fluid Mechanics},\n\tauthor = {Dwivedi, Anubhav and Sidharth, G. S. and Nichols, Joseph W. and Candler, Graham V. and Jovanović, Mihailo R.},\n\tyear = {2019},\n\tnote = {Publisher: Cambridge University Press},\n\tkeywords = {compressible boundary layers, high-speed flow, transition to turbulence},\n\tpages = {113--135},\n}\n\n\n\n
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\n We employ global input–output analysis to quantify amplification of exogenous disturbances in compressible boundary layer flows. Using the spatial structure of the dominant response to time-periodic inputs, we explain the origin of steady reattachment streaks in a hypersonic flow over a compression ramp. Our analysis of the laminar shock–boundary layer interaction reveals that the streaks arise from a preferential amplification of upstream counter-rotating vortical perturbations with a specific spanwise wavelength. These streaks are associated with heat-flux striations at the wall near flow reattachment and they can trigger transition to turbulence. The streak wavelength predicted by our analysis compares favourably with observations from two different hypersonic compression ramp experiments. Furthermore, our analysis of inviscid transport equations demonstrates that base-flow deceleration contributes to the amplification of streamwise velocity and that the baroclinic effects are responsible for the production of streamwise vorticity. Finally, the appearance of the temperature streaks near reattachment is triggered by the growth of streamwise velocity and streamwise vorticity perturbations as well as by the amplification of upstream temperature perturbations by the reattachment shock.\n
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\n \n\n \n \n Hanquist, K. M.; and Boyd, I. D.\n\n\n \n \n \n \n Plasma Assisted Cooling of Hot Surfaces on Hypersonic Vehicles.\n \n \n \n\n\n \n\n\n\n Frontiers in Physics: Plasma for Aerospace, 7(9): 1–13. 2019.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n  \n \n 2 downloads\n \n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{hanquist2019c,\n\ttitle = {Plasma {Assisted} {Cooling} of {Hot} {Surfaces} on {Hypersonic} {Vehicles}},\n\tvolume = {7},\n\tdoi = {10.3389/fphy.2019.00009},\n\tabstract = {Electron transpiration cooling (ETC) is a proposed thermal management approach for the leading edges of hypersonic vehicles that utilizes thermionic emission to emit electrons to carry heat away from the surface. A modeling approach is presented for assessing ETC in a computational fluid dynamics (CFD) framework and is evaluated using previously completed experiments. The modeling approach presented includes developing boundary conditions to account for space-charge-limited emission to accurately determine the level of electron emission from the surface. The effectiveness of ETC for multiple test cases are investigated including sharp leading edges and blunt bodies. For each of these test cases, ETC affects the surface properties, most notably the surface temperature, suggesting that ETC occurs for bodies in thermally intense, ionized flows, no matter the shape of the leading edge. An approximate approach is also presented to assess ETC in an ionized flow and compares its cooling power to radiative cooling.},\n\tnumber = {9},\n\tjournal = {Frontiers in Physics: Plasma for Aerospace},\n\tauthor = {Hanquist, Kyle M. and Boyd, Iain D.},\n\tyear = {2019},\n\tkeywords = {Computational fluid dynamics, Electron transpiration cooling, Hypersonics, Plasma sheath, Thermionic emission, etc, own},\n\tpages = {1--13},\n}\n\n\n\n
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\n Electron transpiration cooling (ETC) is a proposed thermal management approach for the leading edges of hypersonic vehicles that utilizes thermionic emission to emit electrons to carry heat away from the surface. A modeling approach is presented for assessing ETC in a computational fluid dynamics (CFD) framework and is evaluated using previously completed experiments. The modeling approach presented includes developing boundary conditions to account for space-charge-limited emission to accurately determine the level of electron emission from the surface. The effectiveness of ETC for multiple test cases are investigated including sharp leading edges and blunt bodies. For each of these test cases, ETC affects the surface properties, most notably the surface temperature, suggesting that ETC occurs for bodies in thermally intense, ionized flows, no matter the shape of the leading edge. An approximate approach is also presented to assess ETC in an ionized flow and compares its cooling power to radiative cooling.\n
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\n \n\n \n \n Candler, G. V.\n\n\n \n \n \n \n Rate Effects in Hypersonic Flows.\n \n \n \n\n\n \n\n\n\n Annual Review of Fluid Mechanics, 51(1): 379–402. 2019.\n Publisher: Annual Reviews Inc.\n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{candler2019,\n\ttitle = {Rate {Effects} in {Hypersonic} {Flows}},\n\tvolume = {51},\n\tissn = {0066-4189},\n\tdoi = {10.1146/annurev-fluid-010518-040258},\n\tabstract = {Hypersonic flows are energetic and result in regions of high temperature, causing internal energy excitation, chemical reactions, ionization, and gas-surface interactions. At typical flight conditions, the rates of these processes are often similar to the rate of fluid motion. Thus, the gas state is out of local thermodynamic equilibrium and must be described by conservation equations for the internal energy and chemical state. Examples illustrate how competition between rates in hypersonic flows can affect aerodynamic performance, convective heating, boundary layer transition, and ablation. The conservation equations are outlined, and the most widely used models for internal energy relaxation, reaction rates, and transport properties are reviewed. Gas-surface boundary conditions are described, including finite-rate catalysis and slip effects. Recent progress in the use of first-principles calculations to understand and quantify critical gas-phase reactions is discussed. An advanced finite-rate carbon ablation model is introduced and is used to illustrate the role of rate processes at hypersonic conditions.},\n\tnumber = {1},\n\turldate = {2021-02-15},\n\tjournal = {Annual Review of Fluid Mechanics},\n\tauthor = {Candler, Graham V.},\n\tyear = {2019},\n\tnote = {Publisher: Annual Reviews Inc.},\n\tkeywords = {aerothermodynamics, finite-rate processes, high-temperature gas dynamics, hypersonic aerodynamics, nonequilibrium flows},\n\tpages = {379--402},\n}\n\n\n\n
\n
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\n Hypersonic flows are energetic and result in regions of high temperature, causing internal energy excitation, chemical reactions, ionization, and gas-surface interactions. At typical flight conditions, the rates of these processes are often similar to the rate of fluid motion. Thus, the gas state is out of local thermodynamic equilibrium and must be described by conservation equations for the internal energy and chemical state. Examples illustrate how competition between rates in hypersonic flows can affect aerodynamic performance, convective heating, boundary layer transition, and ablation. The conservation equations are outlined, and the most widely used models for internal energy relaxation, reaction rates, and transport properties are reviewed. Gas-surface boundary conditions are described, including finite-rate catalysis and slip effects. Recent progress in the use of first-principles calculations to understand and quantify critical gas-phase reactions is discussed. An advanced finite-rate carbon ablation model is introduced and is used to illustrate the role of rate processes at hypersonic conditions.\n
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\n \n\n \n \n Raissi, M; Perdikaris, P; and Karniadakis, G E\n\n\n \n \n \n \n Physics-informed neural networks: A deep learning framework for solving forward and inverse problems involving nonlinear partial differential equations.\n \n \n \n\n\n \n\n\n\n Journal of Computational Physics, 378. 2019.\n \n\n\n\n
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\n 
@article{raissi2019,\n\ttitle = {Physics-informed neural networks: {A} deep learning framework for solving forward and inverse problems involving nonlinear partial differential equations},\n\tvolume = {378},\n\tjournal = {Journal of Computational Physics},\n\tauthor = {Raissi, M and Perdikaris, P and Karniadakis, G E},\n\tyear = {2019},\n}\n\n\n\n
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\n \n\n \n \n Brandis, A. M; and Cruden, B. A\n\n\n \n \n \n \n NEQAIR v15.0 Release Notes: Nonequilibrium and Equilibrium Radiative Transport and Spectra Program.\n \n \n \n\n\n \n\n\n\n Technical Report 2019.\n Issue: ARC-E-DAA-TN72963\n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@techreport{brandis2019,\n\ttitle = {{NEQAIR} v15.0 {Release} {Notes}: {Nonequilibrium} and {Equilibrium} {Radiative} {Transport} and {Spectra} {Program}},\n\tauthor = {Brandis, Aaron M and Cruden, Brett A},\n\tyear = {2019},\n\tnote = {Issue: ARC-E-DAA-TN72963},\n}\n\n\n\n
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\n \n\n \n \n Hanquist, K. M.\n\n\n \n \n \n \n Modeling of Nonequilibrium Gas and Plasma with Applications to Hypersonics.\n \n \n \n\n\n \n\n\n\n 2019.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n\n\n\n
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@misc{hanquist2019a,\n\taddress = {Department of Aerospace Engineering, Penn State University},\n\ttype = {Invited {Seminar}},\n\ttitle = {Modeling of {Nonequilibrium} {Gas} and {Plasma} with {Applications} to {Hypersonics}},\n\tauthor = {Hanquist, Kyle M.},\n\tyear = {2019},\n\tkeywords = {invited, own},\n}\n\n\n\n
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\n \n\n \n \n Josyula, E.; Suchyta, C. J; Vedula, P.; and Burt, J. M\n\n\n \n \n \n \n Multiquantum Transitions in Oxygen and Nitrogen Molecules in Hypersonic Nonequilibrium Flows.\n \n \n \n\n\n \n\n\n\n Journal of Thermophysics and Heat Transfer, 33(2): 378–391. 2019.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{josyula2019,\n\ttitle = {Multiquantum {Transitions} in {Oxygen} and {Nitrogen} {Molecules} in {Hypersonic} {Nonequilibrium} {Flows}},\n\tvolume = {33},\n\tdoi = {10.2514/1.T5444},\n\tnumber = {2},\n\tjournal = {Journal of Thermophysics and Heat Transfer},\n\tauthor = {Josyula, Eswar and Suchyta, Casimir J and Vedula, Prakash and Burt, Jonathan M},\n\tyear = {2019},\n\tpages = {378--391},\n}\n\n\n\n
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\n \n\n \n \n Hanquist, K. M.; and Boyd, I. D.\n\n\n \n \n \n \n Modeling of Electronically Excited Oxygen in O$_{\\textrm{2}}$ -Ar Shock Tube Studies.\n \n \n \n\n\n \n\n\n\n In AIAA Aviation 2019 Forum, 2019. AIAA Paper 2019-3567\n \n\n\n\n
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@inproceedings{hanquist2019b,\n\ttitle = {Modeling of {Electronically} {Excited} {Oxygen} in {O}$_{\\textrm{2}}$ -{Ar} {Shock} {Tube} {Studies}},\n\tdoi = {10.2514/6.2019-3567},\n\tbooktitle = {{AIAA} {Aviation} 2019 {Forum}},\n\tpublisher = {AIAA Paper 2019-3567},\n\tauthor = {Hanquist, Kyle M. and Boyd, Iain D.},\n\tyear = {2019},\n\tkeywords = {own},\n}\n\n\n\n
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\n \n\n \n \n Streicher, J W; Krish, A; Wang, S; Davidson, D F; and Hanson, R K\n\n\n \n \n \n \n Measurements of Oxygen Vibrational Relaxation and Dissociation Using Ultraviolet Laser Absorption in Shock Tube Experiments.\n \n \n \n\n\n \n\n\n\n In pages 1–11, San Diego, CA, January 2019. \\AIAA Paper\\ 2019-0795\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{streicher2019,\n\taddress = {San Diego, CA},\n\ttitle = {Measurements of {Oxygen} {Vibrational} {Relaxation} and {Dissociation} {Using} {Ultraviolet} {Laser} {Absorption} in {Shock} {Tube} {Experiments}},\n\tpublisher = {\\{AIAA Paper\\} 2019-0795},\n\tauthor = {Streicher, J W and Krish, A and Wang, S and Davidson, D F and Hanson, R K},\n\tmonth = jan,\n\tyear = {2019},\n\tpages = {1--11},\n}\n\n\n\n
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\n \n\n \n \n Boccelli, S.; Bariselli, F.; Dias, B.; and Magin, T. E.\n\n\n \n \n \n \n Lagrangian diffusive reactor for detailed thermochemical computations of plasma flows.\n \n \n \n\n\n \n\n\n\n Plasma Sources Science and Technology, 28(6). June 2019.\n Publisher: IOP Publishing\n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{boccelli2019,\n\ttitle = {Lagrangian diffusive reactor for detailed thermochemical computations of plasma flows},\n\tvolume = {28},\n\tdoi = {10.1088/1361-6595/AB09B5},\n\tabstract = {The simulation of a thermochemical nonequilibrium for atomic and molecular energy level populations in plasma flows requires a comprehensive modeling of all the elementary collisional and radiative processes involved. Coupling detailed chemical mechanisms to flow solvers is computationally expensive and often limits their application to 1D simulations. We develop an efficient Lagrangian diffusive reactor moving along the streamlines of a steady baseline flow simulation to compute detailed thermochemical effects. In addition to its efficiency, the method allows us to model both continuum and rarefied flows, while including mass and energy diffusion. The Lagrangian solver is assessed for several testcases including strong normal shockwaves, as well as 2D and axisymmetric blunt-body hypersonic rarefied flows. In all the testcases performed, the Lagrangian reactor improves drastically the baseline simulations. The computational cost of a Lagrangian recomputation is typically orders of magnitude smaller with respect to a full solution of the problem. The solver has the additional benefit of being immune from statistical noise, which strongly affects the accuracy of calculations obtained by means of the Direct Simulation Monte Carlo method, especially considering minor species in the mixture. The results demonstrate that the method enables applying detailed mechanisms to multidimensional solvers to study thermochemical nonequilibrium flows.},\n\tnumber = {6},\n\tjournal = {Plasma Sources Science and Technology},\n\tauthor = {Boccelli, Stefano and Bariselli, Federico and Dias, Bruno and Magin, Thierry E.},\n\tmonth = jun,\n\tyear = {2019},\n\tnote = {Publisher: IOP Publishing},\n\tkeywords = {Lagrangian chemical reactor, Nonequilibrium plasmas, chemically reactive flows, rarefied gas dynamics},\n}\n\n\n\n
\n
\n\n\n
\n The simulation of a thermochemical nonequilibrium for atomic and molecular energy level populations in plasma flows requires a comprehensive modeling of all the elementary collisional and radiative processes involved. Coupling detailed chemical mechanisms to flow solvers is computationally expensive and often limits their application to 1D simulations. We develop an efficient Lagrangian diffusive reactor moving along the streamlines of a steady baseline flow simulation to compute detailed thermochemical effects. In addition to its efficiency, the method allows us to model both continuum and rarefied flows, while including mass and energy diffusion. The Lagrangian solver is assessed for several testcases including strong normal shockwaves, as well as 2D and axisymmetric blunt-body hypersonic rarefied flows. In all the testcases performed, the Lagrangian reactor improves drastically the baseline simulations. The computational cost of a Lagrangian recomputation is typically orders of magnitude smaller with respect to a full solution of the problem. The solver has the additional benefit of being immune from statistical noise, which strongly affects the accuracy of calculations obtained by means of the Direct Simulation Monte Carlo method, especially considering minor species in the mixture. The results demonstrate that the method enables applying detailed mechanisms to multidimensional solvers to study thermochemical nonequilibrium flows.\n
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\n \n\n \n \n Niu, Q.; Yuan, Z.; Chen, B.; and Dong, S.\n\n\n \n \n \n \n Infrared radiation characteristics of a hypersonic vehicle under time-varying angles of attack.\n \n \n \n\n\n \n\n\n\n Chinese Journal of Aeronautics, 32(4): 861–874. 2019.\n Publisher: Chinese Journal of Aeronautics\n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{niu2019,\n\ttitle = {Infrared radiation characteristics of a hypersonic vehicle under time-varying angles of attack},\n\tvolume = {32},\n\tdoi = {10.1016/j.cja.2019.01.003},\n\tabstract = {Hypersonic vehicles emit strong infrared (IR) radiation signatures that can be treated as a detecting source for object identification and routine diagnosis. This paper is aimed at examining the intrinsic radiation characteristics of a Boost-Glide Vehicle (BGV) under the condition of various Angles of Attack (AOAs). A two-temperature model considering the thermal and chemical non-equilibrium effects is coupled with Navier-Stokes equations solved by the finite volume technique. A gas–solid conjunction heat transfer model is also added into the fluid solver to simulate the surface temperature of the vehicle. The radiative transfer equation is solved with Line of Sight (LOS) algorithm. The computational results for a Hypersonic Technology Vehicle-2 (HTV-2) type vehicle show that radiances of the vehicle are strongly dependent on the surface temperature. The presence of AOA results in the significant difference of the surface temperature. Infrared radiation characteristics are also changed in intensity and spectral band due to the AOA. Simulations are performed with two time-varying AOAs. Transient results indicate that the variation of AOA does have a great effect on the infrared radiance and is closely related to observation angle, spectral band, angle size, angular velocity and time history.},\n\tnumber = {4},\n\tjournal = {Chinese Journal of Aeronautics},\n\tauthor = {Niu, Qinglin and Yuan, Zhichao and Chen, Biao and Dong, Shikui},\n\tyear = {2019},\n\tnote = {Publisher: Chinese Journal of Aeronautics},\n\tkeywords = {Angle of attack, Fluid-thermal interaction, HTV-2, Hypersonic vehicle, IR radiation, Surface temperature},\n\tpages = {861--874},\n}\n\n\n\n
\n
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\n Hypersonic vehicles emit strong infrared (IR) radiation signatures that can be treated as a detecting source for object identification and routine diagnosis. This paper is aimed at examining the intrinsic radiation characteristics of a Boost-Glide Vehicle (BGV) under the condition of various Angles of Attack (AOAs). A two-temperature model considering the thermal and chemical non-equilibrium effects is coupled with Navier-Stokes equations solved by the finite volume technique. A gas–solid conjunction heat transfer model is also added into the fluid solver to simulate the surface temperature of the vehicle. The radiative transfer equation is solved with Line of Sight (LOS) algorithm. The computational results for a Hypersonic Technology Vehicle-2 (HTV-2) type vehicle show that radiances of the vehicle are strongly dependent on the surface temperature. The presence of AOA results in the significant difference of the surface temperature. Infrared radiation characteristics are also changed in intensity and spectral band due to the AOA. Simulations are performed with two time-varying AOAs. Transient results indicate that the variation of AOA does have a great effect on the infrared radiance and is closely related to observation angle, spectral band, angle size, angular velocity and time history.\n
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\n \n\n \n \n Tropina, A. A; Wu, Y.; Limbach, C. M; and Miles, R. B\n\n\n \n \n \n \n Influence of vibrational non-equilibrium on the polarizability and refraction index in air: computational study.\n \n \n \n\n\n \n\n\n\n Journal of Physics D: Applied Physics, 53(10): 105201–105201. December 2019.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{tropina2019,\n\ttitle = {Influence of vibrational non-equilibrium on the polarizability and refraction index in air: computational study},\n\tvolume = {53},\n\tnumber = {10},\n\tjournal = {Journal of Physics D: Applied Physics},\n\tauthor = {Tropina, Albina A and Wu, Yue and Limbach, Christopher M and Miles, Richard B},\n\tmonth = dec,\n\tyear = {2019},\n\tpages = {105201--105201},\n}\n\n\n\n
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\n \n\n \n \n Rafano Carná, S. F.; and Bevilacqua, R.\n\n\n \n \n \n \n High fidelity model for the atmospheric re-entry of CubeSats equipped with the Drag De-Orbit Device.\n \n \n \n\n\n \n\n\n\n Acta Astronautica, 156: 134–156. March 2019.\n Publisher: Elsevier Ltd\n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{rafanocarna2019,\n\ttitle = {High fidelity model for the atmospheric re-entry of {CubeSats} equipped with the {Drag} {De}-{Orbit} {Device}},\n\tvolume = {156},\n\tdoi = {10.1016/j.actaastro.2018.05.049},\n\tabstract = {The use of CubeSat-like small satellites is growing exponentially nowadays, pushing towards missions of increased complexity, including Earth imaging, commercial communications and astronomical observations. As such, they might require components that may survive the re-entry conditions and reach the ground, posing risks for population and properties, or that are intended to be retrieved. The possibility of demise and ground impact poses many challenges from the modeling standpoint because of the uncertainties associated with both the aero- and the aerothermo-dynamic models of the spacecraft. Several formulations and correlations can be found in the literature. Most of them are derived in dated and difficult-to-access papers and technical reports. This paper collects all the necessary and sufficient models, laws and data to describe in a comprehensive way the re-entry of small satellites. They are presented in an organized fashion, with uniform nomenclature and consistent assumptions in order to provide the smallsats scientific community with a smallsats specific, easy-to-understand and rapid-to-implement tool. Furthermore, the paper originally presents an approximated aero- and aerothermo-dynamic model of the Drag De-Orbit Device, a recently developed drag modulation device for drag-based controlled re-entry of large CubeSats.},\n\tjournal = {Acta Astronautica},\n\tauthor = {Rafano Carná, S. F. and Bevilacqua, R.},\n\tmonth = mar,\n\tyear = {2019},\n\tnote = {Publisher: Elsevier Ltd},\n\tkeywords = {Aerodynamic model, Aerothermodynamic model, Atmospheric re-entry modeling, CubeSats, Drag De-Orbit Device},\n\tpages = {134--156},\n}\n\n\n\n
\n
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\n The use of CubeSat-like small satellites is growing exponentially nowadays, pushing towards missions of increased complexity, including Earth imaging, commercial communications and astronomical observations. As such, they might require components that may survive the re-entry conditions and reach the ground, posing risks for population and properties, or that are intended to be retrieved. The possibility of demise and ground impact poses many challenges from the modeling standpoint because of the uncertainties associated with both the aero- and the aerothermo-dynamic models of the spacecraft. Several formulations and correlations can be found in the literature. Most of them are derived in dated and difficult-to-access papers and technical reports. This paper collects all the necessary and sufficient models, laws and data to describe in a comprehensive way the re-entry of small satellites. They are presented in an organized fashion, with uniform nomenclature and consistent assumptions in order to provide the smallsats scientific community with a smallsats specific, easy-to-understand and rapid-to-implement tool. Furthermore, the paper originally presents an approximated aero- and aerothermo-dynamic model of the Drag De-Orbit Device, a recently developed drag modulation device for drag-based controlled re-entry of large CubeSats.\n
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\n \n\n \n \n Spottswood, S. M.; Beberniss, T. J.; Eason, T. G.; Perez, R. A.; Donbar, J. M.; Ehrhardt, D. A.; and Riley, Z. B.\n\n\n \n \n \n \n Exploring the response of a thin, flexible panel to shock-turbulent boundary-layer interactions.\n \n \n \n\n\n \n\n\n\n Journal of Sound and Vibration, 443: 74–89. March 2019.\n Publisher: Academic Press\n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{spottswood2019,\n\ttitle = {Exploring the response of a thin, flexible panel to shock-turbulent boundary-layer interactions},\n\tvolume = {443},\n\tdoi = {10.1016/J.JSV.2018.11.035},\n\tabstract = {The use of nonlinear, dynamic methods for the simulation of aerospace structures has increased dramatically in recent years [1]; however, very little relevant experimental data exists to properly guide these developments. An experimental campaign was initiated by the AFRL Structural Sciences Center (SSC) for three reasons: (1) to observe and measure the effect of turbulence, shock boundary-layer interactions (SBLI) and heated flow on an aircraft-like panel; (2) to explore severe structural events (dynamic instabilities and material failure); and (3) to refine full-field and non-contacting experimental measurement techniques necessary to characterize the flow environment and structural response. All of the objectives were achieved. The panel response to turbulent, heated flow and sensitivity to panel back-pressure modulation was studied, with large-deformation limit cycle behavior leading to panel failure, observed and measured. For the first time, the 3D Digital Image Correlation (DIC) technique was also used to record the panel behavior while filming through the flow and SBLI environment. Finally, fast reacting pressure sensitive paint (PSP) was used, concurrently with 3D DIC, to record the dynamic pressure across the panel surface.},\n\tjournal = {Journal of Sound and Vibration},\n\tauthor = {Spottswood, S. Michael and Beberniss, Timothy J. and Eason, Thomas G. and Perez, Ricardo A. and Donbar, Jeffrey M. and Ehrhardt, David A. and Riley, Zachary B.},\n\tmonth = mar,\n\tyear = {2019},\n\tnote = {Publisher: Academic Press},\n\tkeywords = {Fluid-structure interaction, Shock boundary-layer interaction, Sonic fatigue},\n\tpages = {74--89},\n}\n\n\n\n
\n
\n\n\n
\n The use of nonlinear, dynamic methods for the simulation of aerospace structures has increased dramatically in recent years [1]; however, very little relevant experimental data exists to properly guide these developments. An experimental campaign was initiated by the AFRL Structural Sciences Center (SSC) for three reasons: (1) to observe and measure the effect of turbulence, shock boundary-layer interactions (SBLI) and heated flow on an aircraft-like panel; (2) to explore severe structural events (dynamic instabilities and material failure); and (3) to refine full-field and non-contacting experimental measurement techniques necessary to characterize the flow environment and structural response. All of the objectives were achieved. The panel response to turbulent, heated flow and sensitivity to panel back-pressure modulation was studied, with large-deformation limit cycle behavior leading to panel failure, observed and measured. For the first time, the 3D Digital Image Correlation (DIC) technique was also used to record the panel behavior while filming through the flow and SBLI environment. Finally, fast reacting pressure sensitive paint (PSP) was used, concurrently with 3D DIC, to record the dynamic pressure across the panel surface.\n
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\n \n\n \n \n Thompson, R. L.; Mishra, A. A.; Iaccarino, G.; Edeling, W.; and Sampaio, L.\n\n\n \n \n \n \n \n Eigenvector perturbation methodology for uncertainty quantification of turbulence models.\n \n \n \n \n\n\n \n\n\n\n Physical Review Fluids, 4(4): 044603–044603. April 2019.\n Publisher: American Physical Society\n\n\n\n
\n\n\n\n \n \n \"EigenvectorPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{thompson2019,\n\ttitle = {Eigenvector perturbation methodology for uncertainty quantification of turbulence models},\n\tvolume = {4},\n\turl = {https://journals.aps.org/prfluids/abstract/10.1103/PhysRevFluids.4.044603},\n\tdoi = {10.1103/PHYSREVFLUIDS.4.044603/FIGURES/9/MEDIUM},\n\tabstract = {Reynolds-averaged Navier-Stokes (RANS) models are the primary numerical recourse to investigate complex engineering turbulent flows in industrial applications. However, to establish RANS models as reliable design tools, it is essential to provide estimates for the uncertainty in their predictions. In the recent past, an uncertainty estimation framework relying on eigenvalue and eigenvector perturbations to the modeled Reynolds stress tensor has been widely applied with satisfactory results. However, the methodology for the eigenvector perturbations is not well established. Evaluations using only eigenvalue perturbations do not provide comprehensive estimates of model form uncertainty, especially in flows with streamline curvature, recirculation, or flow separation. In this article, we outline a methodology for the eigenvector perturbations using a predictor-corrector approach, which uses the incipient eigenvalue perturbations along with the Reynolds stress transport equations to determine the eigenvector perturbations. This approach was applied to benchmark cases of complex turbulent flows. The uncertainty intervals estimated using the proposed framework exhibited substantial improvement over eigenvalue-only perturbations and are able to account for a significant proportion of the discrepancy between RANS predictions and high-fidelity data.},\n\tnumber = {4},\n\tjournal = {Physical Review Fluids},\n\tauthor = {Thompson, Roney L. and Mishra, Aashwin Ananda and Iaccarino, Gianluca and Edeling, Wouter and Sampaio, Luiz},\n\tmonth = apr,\n\tyear = {2019},\n\tnote = {Publisher: American Physical Society},\n\tpages = {044603--044603},\n}\n\n\n\n
\n
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\n Reynolds-averaged Navier-Stokes (RANS) models are the primary numerical recourse to investigate complex engineering turbulent flows in industrial applications. However, to establish RANS models as reliable design tools, it is essential to provide estimates for the uncertainty in their predictions. In the recent past, an uncertainty estimation framework relying on eigenvalue and eigenvector perturbations to the modeled Reynolds stress tensor has been widely applied with satisfactory results. However, the methodology for the eigenvector perturbations is not well established. Evaluations using only eigenvalue perturbations do not provide comprehensive estimates of model form uncertainty, especially in flows with streamline curvature, recirculation, or flow separation. In this article, we outline a methodology for the eigenvector perturbations using a predictor-corrector approach, which uses the incipient eigenvalue perturbations along with the Reynolds stress transport equations to determine the eigenvector perturbations. This approach was applied to benchmark cases of complex turbulent flows. The uncertainty intervals estimated using the proposed framework exhibited substantial improvement over eigenvalue-only perturbations and are able to account for a significant proportion of the discrepancy between RANS predictions and high-fidelity data.\n
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\n \n\n \n \n Plimpton, S. J.; Moore, S. G.; Borner, A.; Stagg, A. K.; Koehler, T. P.; Torczynski, J. R.; and Gallis, M. A.\n\n\n \n \n \n \n Direct simulation Monte Carlo on petaflop supercomputers and beyond.\n \n \n \n\n\n \n\n\n\n Physics of Fluids, 31(8): 086101–086101. August 2019.\n Publisher: AIP Publishing LLCAIP Publishing\n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{plimpton2019,\n\ttitle = {Direct simulation {Monte} {Carlo} on petaflop supercomputers and beyond},\n\tvolume = {31},\n\tdoi = {10.1063/1.5108534},\n\tabstract = {The gold-standard definition of the Direct Simulation Monte Carlo (DSMC) method is given in the 1994 book by Bird [Molecular Gas Dynamics and the Direct Simulation of Gas Flows (Clarendon Press, Ox...},\n\tnumber = {8},\n\tjournal = {Physics of Fluids},\n\tauthor = {Plimpton, S. J. and Moore, S. G. and Borner, A. and Stagg, A. K. and Koehler, T. P. and Torczynski, J. R. and Gallis, M. A.},\n\tmonth = aug,\n\tyear = {2019},\n\tnote = {Publisher: AIP Publishing LLCAIP Publishing},\n\tkeywords = {Monte Carlo methods, flow simulation, rarefied fluid dynamics},\n\tpages = {086101--086101},\n}\n\n\n\n
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\n The gold-standard definition of the Direct Simulation Monte Carlo (DSMC) method is given in the 1994 book by Bird [Molecular Gas Dynamics and the Direct Simulation of Gas Flows (Clarendon Press, Ox...\n
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\n \n\n \n \n Holloway, M. E.; Hanquist, K. M.; and Boyd, I. D.\n\n\n \n \n \n \n Effect of Thermochemistry Modeling on Hypersonic Flow Over a Double Cone.\n \n \n \n\n\n \n\n\n\n In AIAA SCITECH 2019 Forum, 2019. AIAA Paper 2019-2281\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n\n\n\n
\n 
@inproceedings{holloway2019b,\n\ttitle = {Effect of {Thermochemistry} {Modeling} on {Hypersonic} {Flow} {Over} a {Double} {Cone}},\n\tdoi = {10.2514/6.2019-2281},\n\tabstract = {The influence of different assumptions for thermochemistry modeling in hypersonic flow over a double-cone geometry is investigated. The double-cone geometry is simple but produces a complex shock wave/boundary layer interaction and nonequilibrium flow physics. This interaction sig-nificantly impacts the aerothermodynamic loading, in terms of surface pressure and heat transfer. Therefore, it is important that these interactions can be predicted with physical accuracy and numerical efficiency. A CFD analysis is used to study the double-cone in three different thermochemical cases: nonequilibrium flow, equilibrium flow, and frozen flow for five different mixtures of nitrogen and oxygen. Specific areas of interest include the thermochemistry model effects on the flow field and surface properties. The resulting aerodynamic loads are compared to experiments and indicate that thermochemistry modeling assumptions play a significant role in determining surface properties. It is also shown that heat loading is more sensitive to thermochemical modeling than drag and suggests that an accurate measurement of surface heat transfer is of particular interest. Careful analysis also reveals that high enthalpy and pure oxygen flows are particularly sensitive to the thermochemistry model assumed.},\n\tbooktitle = {{AIAA} {SCITECH} 2019 {Forum}},\n\tpublisher = {AIAA Paper 2019-2281},\n\tauthor = {Holloway, Michael E. and Hanquist, Kyle M. and Boyd, Iain D.},\n\tyear = {2019},\n\tkeywords = {own},\n}\n\n\n\n
\n
\n\n\n
\n The influence of different assumptions for thermochemistry modeling in hypersonic flow over a double-cone geometry is investigated. The double-cone geometry is simple but produces a complex shock wave/boundary layer interaction and nonequilibrium flow physics. This interaction sig-nificantly impacts the aerothermodynamic loading, in terms of surface pressure and heat transfer. Therefore, it is important that these interactions can be predicted with physical accuracy and numerical efficiency. A CFD analysis is used to study the double-cone in three different thermochemical cases: nonequilibrium flow, equilibrium flow, and frozen flow for five different mixtures of nitrogen and oxygen. Specific areas of interest include the thermochemistry model effects on the flow field and surface properties. The resulting aerodynamic loads are compared to experiments and indicate that thermochemistry modeling assumptions play a significant role in determining surface properties. It is also shown that heat loading is more sensitive to thermochemical modeling than drag and suggests that an accurate measurement of surface heat transfer is of particular interest. Careful analysis also reveals that high enthalpy and pure oxygen flows are particularly sensitive to the thermochemistry model assumed.\n
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\n \n\n \n \n Brune, A. J.; Bruce, W. E.; Glass, D. E.; and Splinter, S. C.\n\n\n \n \n \n \n Computational predictions of the hypersonic material environmental test system arcjet facility.\n \n \n \n\n\n \n\n\n\n Journal of Thermophysics and Heat Transfer, 33(1): 199–209. September 2019.\n Publisher: American Institute of Aeronautics and Astronautics Inc.\n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{brune2019,\n\ttitle = {Computational predictions of the hypersonic material environmental test system arcjet facility},\n\tvolume = {33},\n\tdoi = {10.2514/1.T5490/ASSET/IMAGES/LARGE/FIGURE15.JPEG},\n\tabstract = {The Hypersonic Materials Environmental Test System arcjet facility located at theNASALangley Research Center in Hampton, Virginia, is primarily used for the research, development, and evaluation of high-temperature thermal protection systems for hypersonic vehicles and reentry systems. To improve testing capabilities and knowledge of the test article environment, a detailed three-dimensional model of the arcjet nozzle and the freejet portion of the flowfield is developed. The computational fluid dynamics model takes into account nonuniform inflow state profiles at the nozzle inlet as well as catalytic recombination efficiency effects at the probe surface. The results of the numerical simulations are compared to the calibrated pitot pressure and the stagnation-point heat flux for three test conditions at low, medium, and high enthalpies. Comparing the results and the test data indicates a partially catalytic copper surface on the heat flux probe of about 10\\% recombination efficiency and a 2-3 kPa pressure drop from the total pressure measured at the plenum section in front of the nozzle. With these assumptions, the predictions are within the uncertainty of the stagnation pressure and heat flux measurements. The predicted velocity conditions at the nozzle exit are also compared and show good agreement with the radial and axial velocimetry data.},\n\tnumber = {1},\n\tjournal = {Journal of Thermophysics and Heat Transfer},\n\tauthor = {Brune, Andrew J. and Bruce, Walter E. and Glass, David E. and Splinter, Scott C.},\n\tmonth = sep,\n\tyear = {2019},\n\tnote = {Publisher: American Institute of Aeronautics and Astronautics Inc.},\n\tkeywords = {Catalysis, Enthalpy, Heat Flux, Hypersonic Vehicles, Molecular Tagging Velocimetry, NASA Langley Research Center, Numerical Simulation, Slug Calorimeters, Stagnation Temperature, Thermal Protection System},\n\tpages = {199--209},\n}\n\n\n\n
\n
\n\n\n
\n The Hypersonic Materials Environmental Test System arcjet facility located at theNASALangley Research Center in Hampton, Virginia, is primarily used for the research, development, and evaluation of high-temperature thermal protection systems for hypersonic vehicles and reentry systems. To improve testing capabilities and knowledge of the test article environment, a detailed three-dimensional model of the arcjet nozzle and the freejet portion of the flowfield is developed. The computational fluid dynamics model takes into account nonuniform inflow state profiles at the nozzle inlet as well as catalytic recombination efficiency effects at the probe surface. The results of the numerical simulations are compared to the calibrated pitot pressure and the stagnation-point heat flux for three test conditions at low, medium, and high enthalpies. Comparing the results and the test data indicates a partially catalytic copper surface on the heat flux probe of about 10% recombination efficiency and a 2-3 kPa pressure drop from the total pressure measured at the plenum section in front of the nozzle. With these assumptions, the predictions are within the uncertainty of the stagnation pressure and heat flux measurements. The predicted velocity conditions at the nozzle exit are also compared and show good agreement with the radial and axial velocimetry data.\n
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\n \n\n \n \n Mackey, L. E.; and Boyd, I. D.\n\n\n \n \n \n \n \n Assessment of hypersonic flow physics on aero-optics.\n \n \n \n \n\n\n \n\n\n\n AIAA Journal, 57(9): 3885–3897. July 2019.\n Publisher: American Institute of Aeronautics and Astronautics Inc.\n\n\n\n
\n\n\n\n \n \n \"AssessmentPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{mackey2019a,\n\ttitle = {Assessment of hypersonic flow physics on aero-optics},\n\tvolume = {57},\n\tissn = {00011452},\n\turl = {http://arc.aiaa.org},\n\tdoi = {10.2514/1.J057869},\n\tabstract = {In a hypersonic environment, the high kinetic energy of the oncoming flow causes the molecules in the flow to be thermally excited, leadingto dissociation. In such a flow field, an aero-optical analysis that considers thermochemical nonequilibrium may be necessary to assist in sensor design. The present study assesses the optical properties of a nonequilibrium, real gas flow field around a hemisphere cylinder. The simulations are conducted at freestream Mach numbers of 11, 13, and 15. The optical distortions are quantified using optical path length and optical path difference. Optical distortion isalso predicted using a perfect gas assumption, and these distortions are provided for comparison. The primary contributions of nonequilibrium parameters on optical distortion are identified. For all Mach numbers, optical path lengths are higher when the effects of dissociation and vibrational relaxation are included. The computational results show that oxygen dissociation is the dominant nonequilibrium flow phenomena affecting the optical distortion. However, as the freestream Mach number increases, atomic nitrogen begins to have an additional influence on optical aberrations.},\n\tnumber = {9},\n\turldate = {2021-05-31},\n\tjournal = {AIAA Journal},\n\tauthor = {Mackey, Lauren E. and Boyd, Iain D.},\n\tmonth = jul,\n\tyear = {2019},\n\tnote = {Publisher: American Institute of Aeronautics and Astronautics Inc.},\n\tkeywords = {Chemical Energy, Computational Fluid Dynamics Simulation, Energy Distribution, Freestream Mach Number, Gas Constant, Nonequilibrium Flows, Optical Properties, Optical Sensor, Stagnation Region, Stagnation Streamlines},\n\tpages = {3885--3897},\n}\n\n\n\n
\n
\n\n\n
\n In a hypersonic environment, the high kinetic energy of the oncoming flow causes the molecules in the flow to be thermally excited, leadingto dissociation. In such a flow field, an aero-optical analysis that considers thermochemical nonequilibrium may be necessary to assist in sensor design. The present study assesses the optical properties of a nonequilibrium, real gas flow field around a hemisphere cylinder. The simulations are conducted at freestream Mach numbers of 11, 13, and 15. The optical distortions are quantified using optical path length and optical path difference. Optical distortion isalso predicted using a perfect gas assumption, and these distortions are provided for comparison. The primary contributions of nonequilibrium parameters on optical distortion are identified. For all Mach numbers, optical path lengths are higher when the effects of dissociation and vibrational relaxation are included. The computational results show that oxygen dissociation is the dominant nonequilibrium flow phenomena affecting the optical distortion. However, as the freestream Mach number increases, atomic nitrogen begins to have an additional influence on optical aberrations.\n
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\n\n\n
\n \n\n \n \n Mackey, L. E.; and Boyd, I. D.\n\n\n \n \n \n \n \n Assessment of hypersonic flow physics on aero-optics.\n \n \n \n \n\n\n \n\n\n\n AIAA Journal, 57(9): 3885–3897. July 2019.\n Publisher: American Institute of Aeronautics and Astronautics Inc.\n\n\n\n
\n\n\n\n \n \n \"AssessmentPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{mackey2019c,\n\ttitle = {Assessment of hypersonic flow physics on aero-optics},\n\tvolume = {57},\n\turl = {http://arc.aiaa.org},\n\tdoi = {10.2514/1.J057869},\n\tabstract = {In a hypersonic environment, the high kinetic energy of the oncoming flow causes the molecules in the flow to be thermally excited, leadingto dissociation. In such a flow field, an aero-optical analysis that considers thermochemical nonequilibrium may be necessary to assist in sensor design. The present study assesses the optical properties of a nonequilibrium, real gas flow field around a hemisphere cylinder. The simulations are conducted at freestream Mach numbers of 11, 13, and 15. The optical distortions are quantified using optical path length and optical path difference. Optical distortion isalso predicted using a perfect gas assumption, and these distortions are provided for comparison. The primary contributions of nonequilibrium parameters on optical distortion are identified. For all Mach numbers, optical path lengths are higher when the effects of dissociation and vibrational relaxation are included. The computational results show that oxygen dissociation is the dominant nonequilibrium flow phenomena affecting the optical distortion. However, as the freestream Mach number increases, atomic nitrogen begins to have an additional influence on optical aberrations.},\n\tnumber = {9},\n\tjournal = {AIAA Journal},\n\tauthor = {Mackey, Lauren E. and Boyd, Iain D.},\n\tmonth = jul,\n\tyear = {2019},\n\tnote = {Publisher: American Institute of Aeronautics and Astronautics Inc.},\n\tkeywords = {Chemical Energy, Computational Fluid Dynamics Simulation, Energy Distribution, Freestream Mach Number, Gas Constant, Nonequilibrium Flows, Optical Properties, Optical Sensor, Stagnation Region, Stagnation Streamlines},\n\tpages = {3885--3897},\n}\n\n\n\n
\n
\n\n\n
\n In a hypersonic environment, the high kinetic energy of the oncoming flow causes the molecules in the flow to be thermally excited, leadingto dissociation. In such a flow field, an aero-optical analysis that considers thermochemical nonequilibrium may be necessary to assist in sensor design. The present study assesses the optical properties of a nonequilibrium, real gas flow field around a hemisphere cylinder. The simulations are conducted at freestream Mach numbers of 11, 13, and 15. The optical distortions are quantified using optical path length and optical path difference. Optical distortion isalso predicted using a perfect gas assumption, and these distortions are provided for comparison. The primary contributions of nonequilibrium parameters on optical distortion are identified. For all Mach numbers, optical path lengths are higher when the effects of dissociation and vibrational relaxation are included. The computational results show that oxygen dissociation is the dominant nonequilibrium flow phenomena affecting the optical distortion. However, as the freestream Mach number increases, atomic nitrogen begins to have an additional influence on optical aberrations.\n
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\n \n\n \n \n Mackey, L. E; and Boyd, I. D\n\n\n \n \n \n \n Assessment of Hypersonic Flow Physics on Aero-Optics.\n \n \n \n\n\n \n\n\n\n AIAA Journal, 57(9): 3885–3897. September 2019.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{mackey2019b,\n\ttitle = {Assessment of {Hypersonic} {Flow} {Physics} on {Aero}-{Optics}},\n\tvolume = {57},\n\tnumber = {9},\n\tjournal = {AIAA Journal},\n\tauthor = {Mackey, Lauren E and Boyd, Iain D},\n\tmonth = sep,\n\tyear = {2019},\n\tpages = {3885--3897},\n}\n\n\n\n
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\n \n\n \n \n Eyi, S.; Hanquist, K. M.; and Boyd, I. D.\n\n\n \n \n \n \n Aerothermodynamic Design Optimization of Hypersonic Vehicles.\n \n \n \n\n\n \n\n\n\n Journal of Thermophysics and Heat Transfer, 33(2): 392–406. 2019.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n  \n \n 4 downloads\n \n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n\n\n\n
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@article{eyi2019b,\n\ttitle = {Aerothermodynamic {Design} {Optimization} of {Hypersonic} {Vehicles}},\n\tvolume = {33},\n\tdoi = {10.2514/1.T5523},\n\tabstract = {The objective of this study is to develop a reliable and efficient design optimization method for hypersonic vehicles focused on aerothermodynamic environments. Considering the nature of hypersonic flight, a high-fidelity aerothermodynamic analysis code is used for the simulation of weakly ionized hypersonic flows in thermochemical nonequilibrium. A gradient-based method is implemented for optimization. Bezier or nonuniform rational basis spline curves are used to parametrize the geometry or the geometry change. Linear elasticity theory is implemented for mesh deformation. Penalty functions are utilized to prevent undesired geometrical changes. The design objective is to minimize drag without increasing the total heat transfer rate and the maximum values of the surface heat flux, temperature, and pressure. Design optimizations are performed at different trajectory points of the IRV-2 vehicle. The effects of parametrizations, the number of design variables, and freestream conditions on design performance are studied.},\n\tnumber = {2},\n\tjournal = {Journal of Thermophysics and Heat Transfer},\n\tauthor = {Eyi, Sinan and Hanquist, Kyle M. and Boyd, Iain D.},\n\tyear = {2019},\n\tkeywords = {own},\n\tpages = {392--406},\n}\n\n\n\n
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\n The objective of this study is to develop a reliable and efficient design optimization method for hypersonic vehicles focused on aerothermodynamic environments. Considering the nature of hypersonic flight, a high-fidelity aerothermodynamic analysis code is used for the simulation of weakly ionized hypersonic flows in thermochemical nonequilibrium. A gradient-based method is implemented for optimization. Bezier or nonuniform rational basis spline curves are used to parametrize the geometry or the geometry change. Linear elasticity theory is implemented for mesh deformation. Penalty functions are utilized to prevent undesired geometrical changes. The design objective is to minimize drag without increasing the total heat transfer rate and the maximum values of the surface heat flux, temperature, and pressure. Design optimizations are performed at different trajectory points of the IRV-2 vehicle. The effects of parametrizations, the number of design variables, and freestream conditions on design performance are studied.\n
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\n \n\n \n \n Di Giorgio, S.; Quagliarella, D.; Pezzella, G.; and Pirozzoli, S.\n\n\n \n \n \n \n An aerothermodynamic design optimization framework for hypersonic vehicles.\n \n \n \n\n\n \n\n\n\n Aerospace Science and Technology, 84: 339–347. January 2019.\n Publisher: Elsevier Masson SAS\n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n\n\n\n
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@article{digiorgio2019,\n\ttitle = {An aerothermodynamic design optimization framework for hypersonic vehicles},\n\tvolume = {84},\n\tdoi = {10.1016/j.ast.2018.09.042},\n\tabstract = {In the aviation field great interest is growing in passengers transportation at hypersonic speed. This requires, however, careful study of the enabling technologies necessary for the optimal design of hypersonic vehicles. In this framework, the present work reports on a highly integrated design environment that has been developed in order to provide an optimization loop for vehicle aerothermodynamic design. It includes modules for geometrical parametrization, automated data transfer between tools, automated execution of computational analysis codes, and design optimization methods. This optimization environment is exploited for the aerodynamic design of an unmanned hypersonic cruiser flying at M∞=8 and 30 km altitude. The original contribution of this work is mainly found in the capability of the developed optimization environment of working simultaneously on shape and topology of the aircraft. The results reported and discussed highlight interesting design capabilities, and promise extension to more challenging and realistic integrated aerothermodynamic design problems.},\n\tjournal = {Aerospace Science and Technology},\n\tauthor = {Di Giorgio, Simone and Quagliarella, Domenico and Pezzella, Giuseppe and Pirozzoli, Sergio},\n\tmonth = jan,\n\tyear = {2019},\n\tnote = {Publisher: Elsevier Masson SAS},\n\tkeywords = {CST, Design optimization, Evolutionary strategies, Hypersonics},\n\tpages = {339--347},\n}\n\n\n\n
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\n\n\n
\n In the aviation field great interest is growing in passengers transportation at hypersonic speed. This requires, however, careful study of the enabling technologies necessary for the optimal design of hypersonic vehicles. In this framework, the present work reports on a highly integrated design environment that has been developed in order to provide an optimization loop for vehicle aerothermodynamic design. It includes modules for geometrical parametrization, automated data transfer between tools, automated execution of computational analysis codes, and design optimization methods. This optimization environment is exploited for the aerodynamic design of an unmanned hypersonic cruiser flying at M∞=8 and 30 km altitude. The original contribution of this work is mainly found in the capability of the developed optimization environment of working simultaneously on shape and topology of the aircraft. The results reported and discussed highlight interesting design capabilities, and promise extension to more challenging and realistic integrated aerothermodynamic design problems.\n
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\n \n\n \n \n Hanquist, K. M.\n\n\n \n \n \n \n Aerothermodynamics of Hypersonic Flight and the Importance of Modeling.\n \n \n \n\n\n \n\n\n\n 2019.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n\n\n\n
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@misc{hanquist2019,\n\taddress = {Department of Aerospace \\& Mechanical Engineering, University of Arizona},\n\ttype = {Invited {Seminar}},\n\ttitle = {Aerothermodynamics of {Hypersonic} {Flight} and the {Importance} of {Modeling}},\n\tauthor = {Hanquist, Kyle M.},\n\tyear = {2019},\n\tkeywords = {invited, own},\n}\n\n\n\n
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\n \n\n \n \n Grover, M. S; Suchyta, C. J; and Josyula, E.\n\n\n \n \n \n \n Ab Initio Based Rate Coefficients for Two-Temperature Nonequilibrium Models in Hypersonic Blunt Body Flow.\n \n \n \n\n\n \n\n\n\n In 2019. \\AIAA Paper\\ 2019-0790\n \n\n\n\n
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@inproceedings{grover2019,\n\ttitle = {Ab {Initio} {Based} {Rate} {Coefficients} for {Two}-{Temperature} {Nonequilibrium} {Models} in {Hypersonic} {Blunt} {Body} {Flow}},\n\tpublisher = {\\{AIAA Paper\\} 2019-0790},\n\tauthor = {Grover, Maninder S and Suchyta, Casimir J and Josyula, Eswar},\n\tyear = {2019},\n}\n\n\n\n
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\n \n\n \n \n Mackey, L. E\n\n\n \n \n \n \n Aero-Optical Assessments of Hypersonic Flowfields.\n \n \n \n\n\n \n\n\n\n . 2019.\n \n\n\n\n
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@article{mackey2019,\n\ttitle = {Aero-{Optical} {Assessments} of {Hypersonic} {Flowfields}},\n\tauthor = {Mackey, Lauren E},\n\tyear = {2019},\n}\n\n\n\n
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\n \n\n \n \n Chen, S. Y.; and Boyd, I. D.\n\n\n \n \n \n \n \n A chemical equilibrium analysis approach to oxidation and nitridation of silicon carbide.\n \n \n \n \n\n\n \n\n\n\n In 2019. American Institute of Aeronautics and Astronautics Inc, AIAA\n \n\n\n\n
\n\n\n\n \n \n \"APaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{chen2019,\n\ttitle = {A chemical equilibrium analysis approach to oxidation and nitridation of silicon carbide},\n\tisbn = {978-1-62410-578-4},\n\turl = {https://arc.aiaa.org/doi/10.2514/6.2019-0243},\n\tdoi = {10.2514/6.2019-0243},\n\tabstract = {Silicon carbide has unique oxidation properties that differ from those of ablative thermal protection materials, forming a stable oxide layer. A general thermodynamic equilibrium approach is presented for analysis of the oxidation and nitridation of silicon carbide, combining mass transport and multi-component equilibrium. Passive-to-active transitions are investigated in diluted oxygen, air, and nitrogen environments, and show good agreement with theory and experiments. Different passive-to-active transition mechanisms are examined for oxidation and nitridation, and oxidation exhibits a bifurcation between passive and active states. The thermodynamics leading to temperature jump are explained in the context of these results, and surface temperatures differ from experimental measurements in the literature to within 8\\%.},\n\tpublisher = {American Institute of Aeronautics and Astronautics Inc, AIAA},\n\tauthor = {Chen, Samuel Y. and Boyd, Iain D.},\n\tyear = {2019},\n}\n\n\n\n
\n
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\n Silicon carbide has unique oxidation properties that differ from those of ablative thermal protection materials, forming a stable oxide layer. A general thermodynamic equilibrium approach is presented for analysis of the oxidation and nitridation of silicon carbide, combining mass transport and multi-component equilibrium. Passive-to-active transitions are investigated in diluted oxygen, air, and nitrogen environments, and show good agreement with theory and experiments. Different passive-to-active transition mechanisms are examined for oxidation and nitridation, and oxidation exhibits a bifurcation between passive and active states. The thermodynamics leading to temperature jump are explained in the context of these results, and surface temperatures differ from experimental measurements in the literature to within 8%.\n
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\n \n\n \n \n Birkan, M.; Sayi, A.; Leyva, I.; and Uribarri, L.\n\n\n \n \n \n \n \n 2019 Electron Transpiration Cooling of Materials.\n \n \n \n \n\n\n \n\n\n\n . 2019.\n Place: Washington, DC\n\n\n\n
\n\n\n\n \n \n \"2019Paper\n  \n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@article{birkan2019,\n\ttitle = {2019 {Electron} {Transpiration} {Cooling} of {Materials}},\n\turl = {https://community.apan.org/wg/afosr/w/researchareas/25542/2019-electron-transpiration-cooling-of-materials/},\n\tauthor = {Birkan, Mitat and Sayi, Ali and Leyva, Ivett and Uribarri, Luke},\n\tyear = {2019},\n\tnote = {Place: Washington, DC},\n}\n\n\n\n
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\n  \n 2018\n \n \n (30)\n \n \n
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\n \n\n \n \n Andrienko, D. A; and Boyd, I. D\n\n\n \n \n \n \n Kinetics of O$_{\\textrm{2}}$–N$_{\\textrm{2}}$ collisions at hypersonic temperatures.\n \n \n \n\n\n \n\n\n\n In Atlanta, GA, June 2018. \\AIAA Paper\\ 2018-3438\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@inproceedings{andrienko2018,\n\taddress = {Atlanta, GA},\n\ttitle = {Kinetics of {O}$_{\\textrm{2}}$--{N}$_{\\textrm{2}}$ collisions at hypersonic temperatures},\n\tpublisher = {\\{AIAA Paper\\} 2018-3438},\n\tauthor = {Andrienko, Daniil A and Boyd, Iain D},\n\tmonth = jun,\n\tyear = {2018},\n}\n\n\n\n
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\n \n\n \n \n Dalle, D.; Rogers, S.; Lee, H.; and Meeroff, J.\n\n\n \n \n \n \n Adjustments and Uncertainty Quantification for SLS Aerodynamic Sectional Loads.\n \n \n \n\n\n \n\n\n\n In AIAA Aviation Forum, June 2018. \n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{dalle2018,\n\ttitle = {Adjustments and {Uncertainty} {Quantification} for {SLS} {Aerodynamic} {Sectional} {Loads}},\n\tdoi = {10.2514/6.2018-3640},\n\tbooktitle = {{AIAA} {Aviation} {Forum}},\n\tauthor = {Dalle, Derek and Rogers, Stuart and Lee, Henry and Meeroff, Jamie},\n\tmonth = jun,\n\tyear = {2018},\n}\n\n\n\n
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\n \n\n \n \n Tropina, A.; Wu, Y.; Limbach, C.; and Miles, R. B\n\n\n \n \n \n \n Aero-optical effects in non-equilibrium air.\n \n \n \n\n\n \n\n\n\n In Atlanta, Georgia, June 2018. AIAA 2018-3904\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{tropina2018,\n\taddress = {Atlanta, Georgia},\n\ttitle = {Aero-optical effects in non-equilibrium air},\n\tdoi = {10.2514/6.2018-3904},\n\tpublisher = {AIAA 2018-3904},\n\tauthor = {Tropina, Albina and Wu, Yue and Limbach, Christopher and Miles, Richard B},\n\tmonth = jun,\n\tyear = {2018},\n}\n\n\n\n
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\n \n\n \n \n Huang, D.; Rokita, T.; and Friedmann, P. P.\n\n\n \n \n \n \n Integrated Aerothermoelastic Analysis Framework with Application to Skin Panels.\n \n \n \n\n\n \n\n\n\n AIAA Journal, 56(11): 4562–4581. 2018.\n Publisher: American Institute of Aeronautics and Astronautics _eprint: https://doi.org/10.2514/1.J056677\n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{huang2018,\n\ttitle = {Integrated {Aerothermoelastic} {Analysis} {Framework} with {Application} to {Skin} {Panels}},\n\tvolume = {56},\n\tdoi = {10.2514/1.J056677},\n\tabstract = {This study describes the development of an integrated aerothermoelastic computational framework. The framework consists of a Navier–Stokes aerodynamic solver based on an Automatic Differentiation flow solver code; a finite element structural solver for moderate deflection of a composite, doubly curved, shallow shell with thermal stress; and a finite element thermal solver for heat transfer in composite shallow shells with nonlinear material properties. The solvers are loosely coupled using a partitioned scheme. An analytical approach is developed to determine the time accuracy and the so-called energy accuracy of a loosely coupled scheme, which serves as a guide for designing schemes having a high convergence rate. The aeroelastic and aerothermoelastic behaviors of two-dimensional and three-dimensional panels are investigated using the computational framework. The effects of the aspect ratio and boundary-layer thickness are found to have significant influence on the critical flutter parameter and the onset time of aerothermoelastic instability.},\n\tnumber = {11},\n\turldate = {2024-06-17},\n\tjournal = {AIAA Journal},\n\tauthor = {Huang, Daning and Rokita, Tomer and Friedmann, Peretz P.},\n\tyear = {2018},\n\tnote = {Publisher: American Institute of Aeronautics and Astronautics\n\\_eprint: https://doi.org/10.2514/1.J056677},\n\tpages = {4562--4581},\n}\n\n\n\n\n\n\n\n
\n
\n\n\n
\n This study describes the development of an integrated aerothermoelastic computational framework. The framework consists of a Navier–Stokes aerodynamic solver based on an Automatic Differentiation flow solver code; a finite element structural solver for moderate deflection of a composite, doubly curved, shallow shell with thermal stress; and a finite element thermal solver for heat transfer in composite shallow shells with nonlinear material properties. The solvers are loosely coupled using a partitioned scheme. An analytical approach is developed to determine the time accuracy and the so-called energy accuracy of a loosely coupled scheme, which serves as a guide for designing schemes having a high convergence rate. The aeroelastic and aerothermoelastic behaviors of two-dimensional and three-dimensional panels are investigated using the computational framework. The effects of the aspect ratio and boundary-layer thickness are found to have significant influence on the critical flutter parameter and the onset time of aerothermoelastic instability.\n
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\n \n\n \n \n Alves, L. L.; Bogaerts, A.; Guerra, V.; and Turner, M. M.\n\n\n \n \n \n \n \n Foundations of modelling of nonequilibrium low-temperature plasmas.\n \n \n \n \n\n\n \n\n\n\n Plasma Sources Science and Technology, 27(2): 023002. February 2018.\n Publisher: IOP Publishing\n\n\n\n
\n\n\n\n \n \n \"FoundationsPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{alves2018,\n\ttitle = {Foundations of modelling of nonequilibrium low-temperature plasmas},\n\tvolume = {27},\n\tissn = {0963-0252},\n\turl = {https://dx.doi.org/10.1088/1361-6595/aaa86d},\n\tdoi = {10.1088/1361-6595/aaa86d},\n\tabstract = {This work explains the need for plasma models, introduces arguments for choosing the type of model that better fits the purpose of each study, and presents the basics of the most common nonequilibrium low-temperature plasma models and the information available from each one, along with an extensive list of references for complementary in-depth reading. The paper presents the following models, organised according to the level of multi-dimensional description of the plasma: kinetic models, based on either a statistical particle-in-cell/Monte-Carlo approach or the solution to the Boltzmann equation (in the latter case, special focus is given to the description of the electron kinetics); multi-fluid models, based on the solution to the hydrodynamic equations; global (spatially-average) models, based on the solution to the particle and energy rate-balance equations for the main plasma species, usually including a very complete reaction chemistry; mesoscopic models for plasma–surface interaction, adopting either a deterministic approach or a stochastic dynamical Monte-Carlo approach. For each plasma model, the paper puts forward the physics context, introduces the fundamental equations, presents advantages and limitations, also from a numerical perspective, and illustrates its application with some examples. Whenever pertinent, the interconnection between models is also discussed, in view of multi-scale hybrid approaches.},\n\tlanguage = {en},\n\tnumber = {2},\n\turldate = {2024-04-24},\n\tjournal = {Plasma Sources Science and Technology},\n\tauthor = {Alves, L. L. and Bogaerts, A. and Guerra, V. and Turner, M. M.},\n\tmonth = feb,\n\tyear = {2018},\n\tnote = {Publisher: IOP Publishing},\n\tpages = {023002},\n}\n\n\n\n
\n
\n\n\n
\n This work explains the need for plasma models, introduces arguments for choosing the type of model that better fits the purpose of each study, and presents the basics of the most common nonequilibrium low-temperature plasma models and the information available from each one, along with an extensive list of references for complementary in-depth reading. The paper presents the following models, organised according to the level of multi-dimensional description of the plasma: kinetic models, based on either a statistical particle-in-cell/Monte-Carlo approach or the solution to the Boltzmann equation (in the latter case, special focus is given to the description of the electron kinetics); multi-fluid models, based on the solution to the hydrodynamic equations; global (spatially-average) models, based on the solution to the particle and energy rate-balance equations for the main plasma species, usually including a very complete reaction chemistry; mesoscopic models for plasma–surface interaction, adopting either a deterministic approach or a stochastic dynamical Monte-Carlo approach. For each plasma model, the paper puts forward the physics context, introduces the fundamental equations, presents advantages and limitations, also from a numerical perspective, and illustrates its application with some examples. Whenever pertinent, the interconnection between models is also discussed, in view of multi-scale hybrid approaches.\n
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\n \n\n \n \n Kraus, B. F.; and Raitses, Y.\n\n\n \n \n \n \n Floating potential of emitting surfaces in plasmas with respect to the space potential.\n \n \n \n\n\n \n\n\n\n Physics of Plasmas, 25(3). March 2018.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{kraus2018,\n\ttitle = {Floating potential of emitting surfaces in plasmas with respect to the space potential},\n\tvolume = {25},\n\tissn = {1070-664X, 1089-7674},\n\tdoi = {10.1063/1.5018335},\n\tabstract = {The potential difference between a floating emitting surface and the plasma surrounding it has been described by several sheath models, including the space-charge-limited sheath, the electron sheath with high emission current, and the inverse sheath produced by charge-exchange ion trapping. Our measurements reveal that each of these models has its own regime of validity. We determine the potential of an emissive filament relative to the plasma potential, emphasizing variations in emitted current density and neutral particle density. The potential of a filament in a diffuse plasma is first shown to vanish, consistent with the electron sheath model and increasing electron emission. In a denser plasma with ample neutral pressure, the floating filament potential is positive, as predicted by a derived ion trapping condition. Lastly, the filament floated negatively in a third plasma, where flowing ions and electrons and nonnegligible electric fields may have disrupted ion trapping. Depending on the regime chosen, emitting surfaces can float positively or negatively with respect to the plasma potential.},\n\tlanguage = {en},\n\tnumber = {3},\n\turldate = {2024-01-24},\n\tjournal = {Physics of Plasmas},\n\tauthor = {Kraus, B. F. and Raitses, Y.},\n\tmonth = mar,\n\tyear = {2018},\n}\n\n\n\n\n\n\n\n\n\n\n\n
\n
\n\n\n
\n The potential difference between a floating emitting surface and the plasma surrounding it has been described by several sheath models, including the space-charge-limited sheath, the electron sheath with high emission current, and the inverse sheath produced by charge-exchange ion trapping. Our measurements reveal that each of these models has its own regime of validity. We determine the potential of an emissive filament relative to the plasma potential, emphasizing variations in emitted current density and neutral particle density. The potential of a filament in a diffuse plasma is first shown to vanish, consistent with the electron sheath model and increasing electron emission. In a denser plasma with ample neutral pressure, the floating filament potential is positive, as predicted by a derived ion trapping condition. Lastly, the filament floated negatively in a third plasma, where flowing ions and electrons and nonnegligible electric fields may have disrupted ion trapping. Depending on the regime chosen, emitting surfaces can float positively or negatively with respect to the plasma potential.\n
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\n \n\n \n \n Liu, K.; Wu, T.; Bourell, D. L.; Tan, Y.; Wang, J.; He, M.; Sun, H.; Shi, Y.; and Chen, J.\n\n\n \n \n \n \n \n Laser additive manufacturing and homogeneous densification of complicated shape SiC ceramic parts.\n \n \n \n \n\n\n \n\n\n\n Ceramics International, 44(17): 21067–21075. December 2018.\n \n\n\n\n
\n\n\n\n \n \n \"LaserPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{liu_laser_2018,\n\ttitle = {Laser additive manufacturing and homogeneous densification of complicated shape {SiC} ceramic parts},\n\tvolume = {44},\n\tissn = {0272-8842},\n\turl = {https://www.sciencedirect.com/science/article/pii/S027288421832203X},\n\tdoi = {10.1016/j.ceramint.2018.08.143},\n\tabstract = {To improve the density of SiC ceramic components with complicated shape built by laser sintering (LS), cold isostatic pressing (CIP) and reaction sintering (RS) were incorporated into the process. In the process of LS/CIP/RS, Phenol formaldehyde resin (PF)-SiC composite powder was prepared by mechanical mixing and cold coating methods, with an optimized content of PF at 18 wt\\%. For the purpose of obtaining improved density of the sintered body after final reaction sintering, carbon black was added into the initial mixed powder. The material preparation, LS forming and densification steps were optimized throughout the whole fabrication process. The final sintered SiC bodies with the bending strength of 292 {\\textasciitilde} 348 MPa and the density of 2.94–2.98 g cm− 3 were prepared using the PF coated SiC-C composite powder and the LS / CIP / RS process. The study further showed a positive and practical approach to fabricate SiC ceramic parts with complicated shape using additive manufacturing technology.},\n\tnumber = {17},\n\turldate = {2023-10-28},\n\tjournal = {Ceramics International},\n\tauthor = {Liu, Kai and Wu, Tian and Bourell, David L. and Tan, Yuanliang and Wang, Jiang and He, Mengqiang and Sun, Huajun and Shi, Yusheng and Chen, Jiaqi},\n\tmonth = dec,\n\tyear = {2018},\n\tkeywords = {A. Material preparation, B. Laser sintering, C. Cold isostatic pressing, D. Reaction sintering, E. Silicon carbide},\n\tpages = {21067--21075},\n}\n\n\n\n
\n
\n\n\n
\n To improve the density of SiC ceramic components with complicated shape built by laser sintering (LS), cold isostatic pressing (CIP) and reaction sintering (RS) were incorporated into the process. In the process of LS/CIP/RS, Phenol formaldehyde resin (PF)-SiC composite powder was prepared by mechanical mixing and cold coating methods, with an optimized content of PF at 18 wt%. For the purpose of obtaining improved density of the sintered body after final reaction sintering, carbon black was added into the initial mixed powder. The material preparation, LS forming and densification steps were optimized throughout the whole fabrication process. The final sintered SiC bodies with the bending strength of 292 ~ 348 MPa and the density of 2.94–2.98 g cm− 3 were prepared using the PF coated SiC-C composite powder and the LS / CIP / RS process. The study further showed a positive and practical approach to fabricate SiC ceramic parts with complicated shape using additive manufacturing technology.\n
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\n \n\n \n \n Carnevale, A. P; and Smith, N.\n\n\n \n \n \n \n Balancing Work and Learning.\n \n \n \n\n\n \n\n\n\n . 2018.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{carnevale2018,\n\ttitle = {Balancing {Work} and {Learning}},\n\tlanguage = {en},\n\tauthor = {Carnevale, Anthony P and Smith, Nicole},\n\tyear = {2018},\n}\n\n\n\n\n\n\n\n
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\n \n\n \n \n Patrick, A.; Borrego, M.; and Prybutok, A.\n\n\n \n \n \n \n Predicting Persistence in Engineering through an Engineering Identity Scale.\n \n \n \n\n\n \n\n\n\n . 2018.\n Publisher: International Journal of Engineering Education\n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{patrick2018,\n\ttitle = {Predicting {Persistence} in {Engineering} through an {Engineering} {Identity} {Scale}},\n\tdoi = {10.15781/T2ZC7SB9J},\n\tlanguage = {en},\n\turldate = {2023-09-08},\n\tauthor = {Patrick, A. and Borrego, M. and Prybutok, A.},\n\tyear = {2018},\n\tnote = {Publisher: International Journal of Engineering Education},\n}\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n
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\n \n\n \n \n Sanchez, R.; Albring, T.; Palacios, R.; Gauger, N. R.; Economon, T. D.; and Alonso, J. J.\n\n\n \n \n \n \n Coupled adjoint-based sensitivities in large-displacement fluid-structure interaction using algorithmic differentiation: Coupled adjoint-based sensitivities in large-displacement fluid-structure interaction using algorithmic differentiation.\n \n \n \n\n\n \n\n\n\n International Journal for Numerical Methods in Engineering, 113(7): 1081–1107. February 2018.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{sanchez2018,\n\ttitle = {Coupled adjoint-based sensitivities in large-displacement fluid-structure interaction using algorithmic differentiation: {Coupled} adjoint-based sensitivities in large-displacement fluid-structure interaction using algorithmic differentiation},\n\tvolume = {113},\n\tissn = {00295981},\n\tshorttitle = {Coupled adjoint-based sensitivities in large-displacement fluid-structure interaction using algorithmic differentiation},\n\tdoi = {10.1002/nme.5700},\n\tabstract = {A methodology for the calculation of gradients with respect to design parameters in general FluidStructure Interaction problems is presented. It is based on fixed-point iterations on the adjoint variables of the coupled system using Algorithmic Differentiation. This removes the need for the construction of the analytic Jacobian for the coupled physical problem, which is the usual limitation for the computation of adjoints in most realistic applications. The formulation is shown to be amenable to partitioned solution methods for the adjoint equations. It also poses no restrictions to the nonlinear physics in either the fluid or structural field, other than the existence of a converged solution to the primal problem from which to compute the adjoints. We demonstrate the applicability of this procedure and the accuracy of the computed gradients on coupled problems involving viscous flows with geometrical and material non-linearities in the structural domain.},\n\tlanguage = {en},\n\tnumber = {7},\n\turldate = {2023-08-07},\n\tjournal = {International Journal for Numerical Methods in Engineering},\n\tauthor = {Sanchez, R. and Albring, T. and Palacios, R. and Gauger, N. R. and Economon, T. D. and Alonso, J. J.},\n\tmonth = feb,\n\tyear = {2018},\n\tpages = {1081--1107},\n}\n\n\n\n\n\n\n\n
\n
\n\n\n
\n A methodology for the calculation of gradients with respect to design parameters in general FluidStructure Interaction problems is presented. It is based on fixed-point iterations on the adjoint variables of the coupled system using Algorithmic Differentiation. This removes the need for the construction of the analytic Jacobian for the coupled physical problem, which is the usual limitation for the computation of adjoints in most realistic applications. The formulation is shown to be amenable to partitioned solution methods for the adjoint equations. It also poses no restrictions to the nonlinear physics in either the fluid or structural field, other than the existence of a converged solution to the primal problem from which to compute the adjoints. We demonstrate the applicability of this procedure and the accuracy of the computed gradients on coupled problems involving viscous flows with geometrical and material non-linearities in the structural domain.\n
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\n \n\n \n \n Turbeville, F. D.; and Schneider, S. P.\n\n\n \n \n \n \n Boundary-Layer Instability on a Slender Cone with Highly Swept Fins.\n \n \n \n\n\n \n\n\n\n In 2018 Fluid Dynamics Conference, Atlanta, Georgia, June 2018. American Institute of Aeronautics and Astronautics\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{turbeville2018,\n\taddress = {Atlanta, Georgia},\n\ttitle = {Boundary-{Layer} {Instability} on a {Slender} {Cone} with {Highly} {Swept} {Fins}},\n\tisbn = {978-1-62410-553-1},\n\tdoi = {10.2514/6.2018-3070},\n\tlanguage = {en},\n\turldate = {2023-06-22},\n\tbooktitle = {2018 {Fluid} {Dynamics} {Conference}},\n\tpublisher = {American Institute of Aeronautics and Astronautics},\n\tauthor = {Turbeville, Franklin D. and Schneider, Steven P.},\n\tmonth = jun,\n\tyear = {2018},\n}\n\n\n\n
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\n \n\n \n \n Bose, S. T.; and Park, G. I.\n\n\n \n \n \n \n Wall-Modeled Large-Eddy Simulation for Complex Turbulent Flows.\n \n \n \n\n\n \n\n\n\n Annual Review of Fluid Mechanics, 50(1): 535–561. January 2018.\n Publisher: Annual Reviews\n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{bose2018,\n\ttitle = {Wall-{Modeled} {Large}-{Eddy} {Simulation} for {Complex} {Turbulent} {Flows}},\n\tvolume = {50},\n\tissn = {0066-4189},\n\tdoi = {10.1146/annurev-fluid-122316-045241},\n\tabstract = {Large-eddy simulation (LES) has proven to be a computationally tractable approach to simulate unsteady turbulent flows. However, prohibitive resolution requirements induced by near-wall eddies in high?Reynolds number boundary layers necessitate the use of wall models or approximate wall boundary conditions. We review recent investigations in wall-modeled LES, including the development of novel approximate boundary conditions and the application of wall models to complex flows (e.g., boundary-layer separation, shock/boundary-layer interactions, transition). We also assess the validity of underlying assumptions in wall-model derivations to elucidate the accuracy of these investigations, and offer suggestions for future studies.},\n\tnumber = {1},\n\turldate = {2023-01-12},\n\tjournal = {Annual Review of Fluid Mechanics},\n\tauthor = {Bose, Sanjeeb T. and Park, George Ilhwan},\n\tmonth = jan,\n\tyear = {2018},\n\tnote = {Publisher: Annual Reviews},\n\tpages = {535--561},\n}\n\n\n\n
\n
\n\n\n
\n Large-eddy simulation (LES) has proven to be a computationally tractable approach to simulate unsteady turbulent flows. However, prohibitive resolution requirements induced by near-wall eddies in high?Reynolds number boundary layers necessitate the use of wall models or approximate wall boundary conditions. We review recent investigations in wall-modeled LES, including the development of novel approximate boundary conditions and the application of wall models to complex flows (e.g., boundary-layer separation, shock/boundary-layer interactions, transition). We also assess the validity of underlying assumptions in wall-model derivations to elucidate the accuracy of these investigations, and offer suggestions for future studies.\n
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\n \n\n \n \n Mackey, L. E.; Boyd, I. D.; Jewell, J. S.; and Leger, T. J.\n\n\n \n \n \n \n \n Turbulent hypersonic flow effects on optical sensor performance.\n \n \n \n \n\n\n \n\n\n\n In 2018. American Institute of Aeronautics and Astronautics Inc, AIAA\n \n\n\n\n
\n\n\n\n \n \n \"TurbulentPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{mackey2018,\n\ttitle = {Turbulent hypersonic flow effects on optical sensor performance},\n\tisbn = {978-1-62410-553-1},\n\turl = {http://arc.aiaa.org},\n\tdoi = {10.2514/6.2018-3712},\n\tabstract = {If an optical signal were to travel through a hypersonic flowfield, the type of high-speed flow analysis required to perform reliable assessments of sensor performance is unclear. In the present study, numerical simulations are utilized to perform implicit large eddy computations of a Mach 4 flow over an adiabatic flat plate. The simulations are run with and without thermochemistry models to determine the effects thermochemical nonequilibrium has on optical distortion. The higher fidelity simulation method of accounting for thermochemical nonequilibrium produces less variation in optical path difference (OPD) across the sensor aperture. The root mean square average of OPD is significantly smaller for the real gas simulation when compared to a perfect gas. These differences in OPD occur because nonequilibrium energy exchanges act to damp out turbulent fluctuations. It is, therefore, necessary to include these physical flow effects in optical assessments to obtain an accurate description of the aero-optic distortions.},\n\tpublisher = {American Institute of Aeronautics and Astronautics Inc, AIAA},\n\tauthor = {Mackey, Lauren E. and Boyd, Iain D. and Jewell, Joseph S. and Leger, Timothy J.},\n\tyear = {2018},\n}\n\n\n\n
\n
\n\n\n
\n If an optical signal were to travel through a hypersonic flowfield, the type of high-speed flow analysis required to perform reliable assessments of sensor performance is unclear. In the present study, numerical simulations are utilized to perform implicit large eddy computations of a Mach 4 flow over an adiabatic flat plate. The simulations are run with and without thermochemistry models to determine the effects thermochemical nonequilibrium has on optical distortion. The higher fidelity simulation method of accounting for thermochemical nonequilibrium produces less variation in optical path difference (OPD) across the sensor aperture. The root mean square average of OPD is significantly smaller for the real gas simulation when compared to a perfect gas. These differences in OPD occur because nonequilibrium energy exchanges act to damp out turbulent fluctuations. It is, therefore, necessary to include these physical flow effects in optical assessments to obtain an accurate description of the aero-optic distortions.\n
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\n \n\n \n \n Kim, J. G.; and Park, G.\n\n\n \n \n \n \n \n Thermochemical nonequilibrium parameter modification of oxygen for a two-temperature model.\n \n \n \n \n\n\n \n\n\n\n Physics of Fluids, 30(1): 016101–016101. January 2018.\n Publisher: AIP Publishing LLCAIP Publishing\n\n\n\n
\n\n\n\n \n \n \"ThermochemicalPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{kim2018,\n\ttitle = {Thermochemical nonequilibrium parameter modification of oxygen for a two-temperature model},\n\tvolume = {30},\n\turl = {https://aip.scitation.org/doi/abs/10.1063/1.4996799},\n\tdoi = {10.1063/1.4996799},\n\tabstract = {Thermochemical nonequilibrium parameters of oxygen, O2, for a two-temperature model are proposed in the present work. The rovibrational nonequilibrium and chemical reactions of three low-lying elec...},\n\tnumber = {1},\n\tjournal = {Physics of Fluids},\n\tauthor = {Kim, Jae Gang and Park, Gisu},\n\tmonth = jan,\n\tyear = {2018},\n\tnote = {Publisher: AIP Publishing LLCAIP Publishing},\n\tkeywords = {oxygen, pipe flow, rotational-vibrational states, shock tubes, shock waves, thermochemistry},\n\tpages = {016101--016101},\n}\n\n\n\n
\n
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\n Thermochemical nonequilibrium parameters of oxygen, O2, for a two-temperature model are proposed in the present work. The rovibrational nonequilibrium and chemical reactions of three low-lying elec...\n
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\n \n\n \n \n Hara, K.; and Hanquist, K. M.\n\n\n \n \n \n \n Test cases for grid-based direct kinetic modeling of plasma flows.\n \n \n \n\n\n \n\n\n\n Plasma Sources Science and Technology, 27(6). 2018.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n  \n \n 1 download\n \n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{hara2018,\n\ttitle = {Test cases for grid-based direct kinetic modeling of plasma flows},\n\tvolume = {27},\n\tdoi = {10.1088/1361-6595/aac6b9},\n\tabstract = {Grid-based kinetic models are promising in that the numerical noise inherent in particle-based methods is essentially eliminated. Here, we call such grid-based techniques a direct kinetic (DK) model. Velocity distribution functions are directly obtained by solving kinetic equations, such as the Vlasov equation, in discretized phase space, i.e., both physical and velocity space. In solving the kinetic equations that are hyperbolic partial differential equations, we employ a conservative, positivity-preserving numerical scheme, which is necessary for robust calculations of problems particularly including ionization. Test cases described in this paper include plasma sheaths with electron emission and injection and expansion of neutral atom flow in a two-dimensional configuration. A unifying kinetic theory of space charge limited sheaths for both floating and conducting surfaces is presented. The improved theory is verified using the collisionless DK simulation, particularly for small sheath potentials that particle-based kinetic simulations may struggle due to statistical noise. For benchmarking of the grid-based and particle-based kinetic simulations, hybrid simulations of Hall thruster discharge plasma are performed. While numerical diffusion occurs in the phase space in the DK simulation, ionization oscillations are well resolved since ionization events can be taken into account deterministically at every time step.},\n\tnumber = {6},\n\tjournal = {Plasma Sources Science and Technology},\n\tauthor = {Hara, Kentaro and Hanquist, Kyle M.},\n\tyear = {2018},\n\tkeywords = {Hall thruster, Kinetic simulation, Vlasov simulation, etc, nonlinear plasma waves, own, plasma instability, plasma sheaths, space charge limited sheath},\n}\n\n\n\n
\n
\n\n\n
\n Grid-based kinetic models are promising in that the numerical noise inherent in particle-based methods is essentially eliminated. Here, we call such grid-based techniques a direct kinetic (DK) model. Velocity distribution functions are directly obtained by solving kinetic equations, such as the Vlasov equation, in discretized phase space, i.e., both physical and velocity space. In solving the kinetic equations that are hyperbolic partial differential equations, we employ a conservative, positivity-preserving numerical scheme, which is necessary for robust calculations of problems particularly including ionization. Test cases described in this paper include plasma sheaths with electron emission and injection and expansion of neutral atom flow in a two-dimensional configuration. A unifying kinetic theory of space charge limited sheaths for both floating and conducting surfaces is presented. The improved theory is verified using the collisionless DK simulation, particularly for small sheath potentials that particle-based kinetic simulations may struggle due to statistical noise. For benchmarking of the grid-based and particle-based kinetic simulations, hybrid simulations of Hall thruster discharge plasma are performed. While numerical diffusion occurs in the phase space in the DK simulation, ionization oscillations are well resolved since ionization events can be taken into account deterministically at every time step.\n
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\n \n\n \n \n Witze, A.\n\n\n \n \n \n \n The Quest to Conquer the Space Junk Problem.\n \n \n \n\n\n \n\n\n\n Nature, 561. 2018.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{witze2018,\n\ttitle = {The {Quest} to {Conquer} the {Space} {Junk} {Problem}},\n\tvolume = {561},\n\tjournal = {Nature},\n\tauthor = {Witze, Alexandra},\n\tyear = {2018},\n}\n\n\n\n
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\n \n\n \n \n Molchanova, A. N.; Kashkovsky, A. V.; and Bondar, Y. A.\n\n\n \n \n \n \n \n Surface recombination in the direct simulation Monte Carlo method.\n \n \n \n \n\n\n \n\n\n\n Physics of Fluids, 30(10): 107105–107105. October 2018.\n Publisher: AIP Publishing LLCAIP Publishing\n\n\n\n
\n\n\n\n \n \n \"SurfacePaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{molchanova2018,\n\ttitle = {Surface recombination in the direct simulation {Monte} {Carlo} method},\n\tvolume = {30},\n\turl = {https://aip.scitation.org/doi/abs/10.1063/1.5048353},\n\tdoi = {10.1063/1.5048353},\n\tabstract = {This work is aimed at the development of surface chemistry models for the Direct Simulation Monte Carlo (DSMC) method applicable to non-equilibrium high-temperature flows about reentry vehicles. Pr...},\n\tnumber = {10},\n\tjournal = {Physics of Fluids},\n\tauthor = {Molchanova, Alexandra N. and Kashkovsky, Alexander V. and Bondar, Yevgeniy A.},\n\tmonth = oct,\n\tyear = {2018},\n\tnote = {Publisher: AIP Publishing LLCAIP Publishing},\n\tpages = {107105--107105},\n}\n\n\n\n
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\n This work is aimed at the development of surface chemistry models for the Direct Simulation Monte Carlo (DSMC) method applicable to non-equilibrium high-temperature flows about reentry vehicles. Pr...\n
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\n \n\n \n \n Chaudhry, R. S.; Bender, J. D.; Schwartzentruber, T. E.; and Candler, G. V.\n\n\n \n \n \n \n \n Quasiclassical trajectory analysis of nitrogen for high-temperature chemical kinetics.\n \n \n \n \n\n\n \n\n\n\n Journal of Thermophysics and Heat Transfer, 32(4): 833–845. September 2018.\n Publisher: American Institute of Aeronautics and Astronautics Inc.\n\n\n\n
\n\n\n\n \n \n \"QuasiclassicalPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{chaudhry2018a,\n\ttitle = {Quasiclassical trajectory analysis of nitrogen for high-temperature chemical kinetics},\n\tvolume = {32},\n\turl = {https://arc.aiaa.org/doi/10.2514/1.T5484},\n\tdoi = {10.2514/1.T5484/ASSET/IMAGES/LARGE/FIGURE12.JPEG},\n\tabstract = {Understanding gas–phase chemical kinetics is important for modeling hypersonic flows. This paper discusses quasiclassical trajectory analysis, in which gas–phase interactions are simulated using ab initio quantum chemistry data. N2 N2, N2 N, and N2 O2 collisions are studied for conditions at thermal equilibrium and nonequilibrium. The nitrogen dissociation rate with all collision partners is found to be similar for a given thermal environment: the largest deviation is 50\\% at thermal nonequilibrium, and at equilibrium the N2 N2 and N2 N rates are within 15\\% of each other. The vibrational energy decrease due to nitrogen dissociation, a necessary input to computational fluid dynamics, also behaves similarly for all collision partners and strongly depends on the degree of thermal nonequilibrium. Using data for nitrogen dissociation and oxygen dissociation with partner N2, the effect of each reactant state on dissociation is quantified. The effect of the collision partner’s internal energy on simple dissociation is found to be small and likely negligible. Finally, the effect of vibrational energy on simple dissociation is found to be stronger than the effect of rotational energy. These rigorous statistical analyses enable the development of physics-based models for computational fluid dynamics.},\n\tnumber = {4},\n\tjournal = {Journal of Thermophysics and Heat Transfer},\n\tauthor = {Chaudhry, Ross S. and Bender, Jason D. and Schwartzentruber, Thomas E. and Candler, Graham V.},\n\tmonth = sep,\n\tyear = {2018},\n\tnote = {Publisher: American Institute of Aeronautics and Astronautics Inc.},\n\tkeywords = {Boltzmann Constant, Born Oppenheimer Approximation, CFD, Energy Distribution, High Temperature Chemical Kinetics, Hypersonic Flows, Internal Energy, Probability Density Functions, Shock Tube, Thermal Nonequilibrium},\n\tpages = {833--845},\n}\n\n\n\n
\n
\n\n\n
\n Understanding gas–phase chemical kinetics is important for modeling hypersonic flows. This paper discusses quasiclassical trajectory analysis, in which gas–phase interactions are simulated using ab initio quantum chemistry data. N2 N2, N2 N, and N2 O2 collisions are studied for conditions at thermal equilibrium and nonequilibrium. The nitrogen dissociation rate with all collision partners is found to be similar for a given thermal environment: the largest deviation is 50% at thermal nonequilibrium, and at equilibrium the N2 N2 and N2 N rates are within 15% of each other. The vibrational energy decrease due to nitrogen dissociation, a necessary input to computational fluid dynamics, also behaves similarly for all collision partners and strongly depends on the degree of thermal nonequilibrium. Using data for nitrogen dissociation and oxygen dissociation with partner N2, the effect of each reactant state on dissociation is quantified. The effect of the collision partner’s internal energy on simple dissociation is found to be small and likely negligible. Finally, the effect of vibrational energy on simple dissociation is found to be stronger than the effect of rotational energy. These rigorous statistical analyses enable the development of physics-based models for computational fluid dynamics.\n
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\n \n\n \n \n Tumuklu, O.; Theofilis, V.; and Levin, D. A.\n\n\n \n \n \n \n On the unsteadiness of shock–laminar boundary layer interactions of hypersonic flows over a double cone.\n \n \n \n\n\n \n\n\n\n Physics of Fluids, 30(10). October 2018.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{tumuklu2018a,\n\ttitle = {On the unsteadiness of shock–laminar boundary layer interactions of hypersonic flows over a double cone},\n\tvolume = {30},\n\tissn = {1070-6631, 1089-7666},\n\tdoi = {10.1063/1.5047791},\n\tlanguage = {en},\n\tnumber = {10},\n\turldate = {2023-05-12},\n\tjournal = {Physics of Fluids},\n\tauthor = {Tumuklu, Ozgur and Theofilis, Vassilis and Levin, Deborah A.},\n\tmonth = oct,\n\tyear = {2018},\n}\n\n\n\n
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\n \n\n \n \n Hanquist, K. M.; and Boyd, I. D.\n\n\n \n \n \n \n Modeling of Excited Oxygen in Post Normal Shock Waves.\n \n \n \n\n\n \n\n\n\n In 2018 Joint Thermophysics and Heat Transfer Conference, 2018. AIAA Paper 2018-3769\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n\n\n\n
\n 
@inproceedings{hanquist2018g,\n\ttitle = {Modeling of {Excited} {Oxygen} in {Post} {Normal} {Shock} {Waves}},\n\tdoi = {10.2514/6.2018-3769},\n\tabstract = {The successful development of hypersonic vehicles requires a detailed knowledge of the flow physics around the vehicle. Specifically, an understanding of the thermochemical nonequilibrium behavior is crucial for this flight regime. The hypersonic flight regime involves an extremely high level of energy, so a small error in the modeling of the energy processes can result in drastic changes in the vehicle design, which motivates modeling the physics involved at a high-fidelity. Recent progress is presented in an ongoing effort to model the excited states of oxygen in post-normal shock waves using computational fluid dynamics. One-dimensional post normal shock flow calculations are carried out using state-of-the-art thermochemical nonequilibrium models. Two-temperature and electronic master equation coupling models are adopted in the present work and discussed in detail. Different approaches of modeling the energy transfer from each mode are also presented. The approaches are assessed using a set of existing experiments where the vibrational temperature was measured. The concentrations of excited states of atomic oxygen determined by the electronic master equation coupling model are compared to Boltzmann distributions.},\n\tbooktitle = {2018 {Joint} {Thermophysics} and {Heat} {Transfer} {Conference}},\n\tpublisher = {AIAA Paper 2018-3769},\n\tauthor = {Hanquist, Kyle M. and Boyd, Iain D.},\n\tyear = {2018},\n\tkeywords = {own},\n}\n\n\n\n
\n
\n\n\n
\n The successful development of hypersonic vehicles requires a detailed knowledge of the flow physics around the vehicle. Specifically, an understanding of the thermochemical nonequilibrium behavior is crucial for this flight regime. The hypersonic flight regime involves an extremely high level of energy, so a small error in the modeling of the energy processes can result in drastic changes in the vehicle design, which motivates modeling the physics involved at a high-fidelity. Recent progress is presented in an ongoing effort to model the excited states of oxygen in post-normal shock waves using computational fluid dynamics. One-dimensional post normal shock flow calculations are carried out using state-of-the-art thermochemical nonequilibrium models. Two-temperature and electronic master equation coupling models are adopted in the present work and discussed in detail. Different approaches of modeling the energy transfer from each mode are also presented. The approaches are assessed using a set of existing experiments where the vibrational temperature was measured. The concentrations of excited states of atomic oxygen determined by the electronic master equation coupling model are compared to Boltzmann distributions.\n
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\n \n\n \n \n Chaudhry, R. S\n\n\n \n \n \n \n Modeling and Analysis of Chemical Kinetics for Hypersonic Flows in Air.\n \n \n \n\n\n \n\n\n\n . 2018.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{chaudhry2018,\n\ttitle = {Modeling and {Analysis} of {Chemical} {Kinetics} for {Hypersonic} {Flows} in {Air}},\n\tauthor = {Chaudhry, Ross S},\n\tyear = {2018},\n}\n\n\n\n
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\n \n\n \n \n Parent, B.; Shneider, M. N; and Macheret, S. O\n\n\n \n \n \n \n Large Eddy Simulation of Boundary Layer Transition Induced by DBD Plasma Actuators.\n \n \n \n\n\n \n\n\n\n In 2018. \n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{parent2018,\n\ttitle = {Large {Eddy} {Simulation} of {Boundary} {Layer} {Transition} {Induced} by {DBD} {Plasma} {Actuators}},\n\tdoi = {10.2514/6.2018-0444},\n\tabstract = {Nomenclature Roman symbols C k = particule charge of kth species, C E = electric field vector, r , V/m n s = number of species (including charged species) N k = species number density, m 3 P k = species partial pressure, Pa P = pressure of mixture, Pa s k = sign of the charge of species k (either C1 for the positive species or 1 for the negative species) T = temperature of mixture, K t = time, s U = flow speed, m/s V n = velocity of the neutrals, m/s x i = Cartesian coordinates, m x; y; z = Cartesian coordinates, m Greek symbols 0 = permittivity of free space, m 3 kg 1 s 4 A 2 r = relative permittivity = conductivity, S/m = electric field potential, V c = net charge density, C m 3 k = mobility of kth species, m 2 /(V s) Subscripts w = at the wall 1 = free stream},\n\tauthor = {Parent, Bernard and Shneider, Mikhail N and Macheret, Sergey O},\n\tyear = {2018},\n}\n\n\n\n
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\n Nomenclature Roman symbols C k = particule charge of kth species, C E = electric field vector, r , V/m n s = number of species (including charged species) N k = species number density, m 3 P k = species partial pressure, Pa P = pressure of mixture, Pa s k = sign of the charge of species k (either C1 for the positive species or 1 for the negative species) T = temperature of mixture, K t = time, s U = flow speed, m/s V n = velocity of the neutrals, m/s x i = Cartesian coordinates, m x; y; z = Cartesian coordinates, m Greek symbols 0 = permittivity of free space, m 3 kg 1 s 4 A 2 r = relative permittivity = conductivity, S/m = electric field potential, V c = net charge density, C m 3 k = mobility of kth species, m 2 /(V s) Subscripts w = at the wall 1 = free stream\n
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\n \n\n \n \n Tumuklu, O.; Levin, D. A.; and Theofilis, V.\n\n\n \n \n \n \n Investigation of unsteady, hypersonic, laminar separated flows over a double cone geometry using a kinetic approach.\n \n \n \n\n\n \n\n\n\n Physics of Fluids, 30(4). 2018.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{tumuklu2018,\n\ttitle = {Investigation of unsteady, hypersonic, laminar separated flows over a double cone geometry using a kinetic approach},\n\tvolume = {30},\n\tissn = {1070-6631, 1089-7666},\n\tdoi = {10.1063/1.5022598},\n\tlanguage = {en},\n\tnumber = {4},\n\turldate = {2023-05-12},\n\tjournal = {Physics of Fluids},\n\tauthor = {Tumuklu, Ozgur and Levin, Deborah A. and Theofilis, Vassilis},\n\tyear = {2018},\n}\n\n\n\n
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\n \n\n \n \n Bhattrai, S.; Mcquellin, L. P; Currao, G. M D; Neely, A. J; and Buttsworth, D. R\n\n\n \n \n \n \n \n Influence of hypersonic fluid-structure interaction on the control authority of a trailing-edge flap.\n \n \n \n \n\n\n \n\n\n\n In 2018. \n \n\n\n\n
\n\n\n\n \n \n \"InfluencePaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{bhattrai2018,\n\ttitle = {Influence of hypersonic fluid-structure interaction on the control authority of a trailing-edge flap},\n\turl = {http://arc.aiaa.org},\n\tdoi = {10.2514/6.2018-5265},\n\tabstract = {This paper describes the numerical and experimental investigation of rigid and compliant hypersonic control flaps undergoing fluid-structure interaction (FSI). The purpose of the study is to investigate experimental techniques that support the evaluation of flight control systems in hypersonic ground test-with the emphasis of providing control to a trailing-edge flap model undergoing FSI. The rigid flap and compliant flap (of 1 mm thickness) were tested at inclination angles of 0 • , 5 • , 10 • , 15 • , and 20 •. Numerical simulations of two-and three-dimensional flow fields were carried-out in US3D, while the experiments were conducted at the University of Southern Queensland hypersonic wind tunnel facility (TUSQ), under the test flow conditions of Mach 5.8, 75 K and 755 Pa. The forces and moments acting on the models-primarily the lift, drag and pitching moment-were measured with a six component load cell. Tests were carried-out both with and without the load cell to observe the models' responses independently. The schlieren method was used to visualize the flow fields. The schlieren images were also used to obtain the flap deformation profile, as well as, the flap trailing-edge oscillation response. Frequency analysis of the complaint flaps was performed with the load cell measurement responses of lift, drag and pitching moment, and schlieren-tracked response of the flap trailing-edge. From the analyses, the load cell was found to have a low-frequency response of its own. In absence of the load cell, the compliant flap trailing-edge oscillation induced a new structural vibration mode that lead to a destructive interference of the oscillation. While, in the presence of the load cell, it's low-rigidity had the effect of damping this induced vibration. The data and analysis presented in this study are also used in designing the future experiments that will implement a software-in-the-loop actuated control of the rigid and compliant flap models.},\n\tauthor = {Bhattrai, Sudip and Mcquellin, Liam P and Currao, Gaetano M D and Neely, Andrew J and Buttsworth, David R},\n\tyear = {2018},\n}\n\n\n\n
\n
\n\n\n
\n This paper describes the numerical and experimental investigation of rigid and compliant hypersonic control flaps undergoing fluid-structure interaction (FSI). The purpose of the study is to investigate experimental techniques that support the evaluation of flight control systems in hypersonic ground test-with the emphasis of providing control to a trailing-edge flap model undergoing FSI. The rigid flap and compliant flap (of 1 mm thickness) were tested at inclination angles of 0 • , 5 • , 10 • , 15 • , and 20 •. Numerical simulations of two-and three-dimensional flow fields were carried-out in US3D, while the experiments were conducted at the University of Southern Queensland hypersonic wind tunnel facility (TUSQ), under the test flow conditions of Mach 5.8, 75 K and 755 Pa. The forces and moments acting on the models-primarily the lift, drag and pitching moment-were measured with a six component load cell. Tests were carried-out both with and without the load cell to observe the models' responses independently. The schlieren method was used to visualize the flow fields. The schlieren images were also used to obtain the flap deformation profile, as well as, the flap trailing-edge oscillation response. Frequency analysis of the complaint flaps was performed with the load cell measurement responses of lift, drag and pitching moment, and schlieren-tracked response of the flap trailing-edge. From the analyses, the load cell was found to have a low-frequency response of its own. In absence of the load cell, the compliant flap trailing-edge oscillation induced a new structural vibration mode that lead to a destructive interference of the oscillation. While, in the presence of the load cell, it's low-rigidity had the effect of damping this induced vibration. The data and analysis presented in this study are also used in designing the future experiments that will implement a software-in-the-loop actuated control of the rigid and compliant flap models.\n
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\n \n\n \n \n Hanquist, K. M.; and Boyd, I. D.\n\n\n \n \n \n \n Effectiveness of Thermionic Emission for Cooling Hypersonic Vehicle Surfaces.\n \n \n \n\n\n \n\n\n\n In AIAA SCITECH 2018 Forum, 2018. AIAA Paper 2018-1714\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n\n\n\n
\n 
@inproceedings{hanquist2018e,\n\ttitle = {Effectiveness of {Thermionic} {Emission} for {Cooling} {Hypersonic} {Vehicle} {Surfaces}},\n\tdoi = {10.2514/6.2018-1714},\n\tabstract = {Electron transpiration cooling (ETC) is a proposed thermal management approach for the leading edges of hypersonic vehicles that utilizes thermionic emission to emit electrons to carry heat away from the surface. This paper presents a modeling approach for implementing ETC in a computational fluid dynamics (CFD) framework and assesses the modeling approach using a set of previously completed experiments. The modeling approach includes coupling the fluid modeling to a material response code to model in-depth surface conduction and accounts for space-charge-limited emission. The effectiveness of ETC for multiple test cases are investigated including a case with a sharp leading edge, case with in-depth material conduction, and a blunt body (i.e. capsule). For each of these test cases, ETC affects the surface properties, most notably the surface temperature, suggesting that ETC occurs for bodies in thermally intense, ionized flows, no matter the shape of the leading edge. An equation is provided to estimate the heat transfer induced by ETC.},\n\tbooktitle = {{AIAA} {SCITECH} 2018 {Forum}},\n\tpublisher = {AIAA Paper 2018-1714},\n\tauthor = {Hanquist, Kyle M. and Boyd, Iain D.},\n\tyear = {2018},\n\tkeywords = {etc, own},\n}\n\n\n\n
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\n Electron transpiration cooling (ETC) is a proposed thermal management approach for the leading edges of hypersonic vehicles that utilizes thermionic emission to emit electrons to carry heat away from the surface. This paper presents a modeling approach for implementing ETC in a computational fluid dynamics (CFD) framework and assesses the modeling approach using a set of previously completed experiments. The modeling approach includes coupling the fluid modeling to a material response code to model in-depth surface conduction and accounts for space-charge-limited emission. The effectiveness of ETC for multiple test cases are investigated including a case with a sharp leading edge, case with in-depth material conduction, and a blunt body (i.e. capsule). For each of these test cases, ETC affects the surface properties, most notably the surface temperature, suggesting that ETC occurs for bodies in thermally intense, ionized flows, no matter the shape of the leading edge. An equation is provided to estimate the heat transfer induced by ETC.\n
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\n \n\n \n \n Manohar, K.; Brunton, B. W.; Kutz, J. N.; and Brunton, S. L.\n\n\n \n \n \n \n Data-Driven Sparse Sensor Placement for Reconstruction: Demonstrating the Benefits of Exploiting Known Patterns.\n \n \n \n\n\n \n\n\n\n IEEE Control Systems, 38(3): 63–86. June 2018.\n Publisher: Institute of Electrical and Electronics Engineers Inc.\n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{manohar2018,\n\ttitle = {Data-{Driven} {Sparse} {Sensor} {Placement} for {Reconstruction}: {Demonstrating} the {Benefits} of {Exploiting} {Known} {Patterns}},\n\tvolume = {38},\n\tdoi = {10.1109/MCS.2018.2810460},\n\tabstract = {Optimal sensor and actuator placement is an important unsolved problem in control theory. Nearly every downstream control decision is affected by these sensor and actuator locations, but determining optimal locations amounts to an intractable brute-force search among the combinatorial possibilities. Indeed, there are (np) = n!/((n-p)!p!) possible choices of p point sensors out of an n-dimensional state x. Determining optimal sensor and actuator placement in general, even for linear feedback control, is an open challenge. Instead, sensor and actuator locations are routinely chosen according to heuristics and intuition. For moderate-sized search spaces, the sensor placement problem has well-known model-based solutions using optimal experiment design [1], [2], and information theoretic and Bayesian criteria [3]-[7]. As discussed in »Summary,» this article explores how to design optimal sensor locations for signal reconstruction in a framework that scales to arbitrarily large problems, leveraging modern techniques in machine learning and sparse sampling. Reducing the number of sensors through principled selection may be critically enabling when sensors are costly, and it may also enable faster state estimation for low-latency, high-bandwidth control.},\n\tnumber = {3},\n\tjournal = {IEEE Control Systems},\n\tauthor = {Manohar, Krithika and Brunton, Bingni W. and Kutz, J. Nathan and Brunton, Steven L.},\n\tmonth = jun,\n\tyear = {2018},\n\tnote = {Publisher: Institute of Electrical and Electronics Engineers Inc.},\n\tpages = {63--86},\n}\n\n\n\n
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\n Optimal sensor and actuator placement is an important unsolved problem in control theory. Nearly every downstream control decision is affected by these sensor and actuator locations, but determining optimal locations amounts to an intractable brute-force search among the combinatorial possibilities. Indeed, there are (np) = n!/((n-p)!p!) possible choices of p point sensors out of an n-dimensional state x. Determining optimal sensor and actuator placement in general, even for linear feedback control, is an open challenge. Instead, sensor and actuator locations are routinely chosen according to heuristics and intuition. For moderate-sized search spaces, the sensor placement problem has well-known model-based solutions using optimal experiment design [1], [2], and information theoretic and Bayesian criteria [3]-[7]. As discussed in »Summary,» this article explores how to design optimal sensor locations for signal reconstruction in a framework that scales to arbitrarily large problems, leveraging modern techniques in machine learning and sparse sampling. Reducing the number of sensors through principled selection may be critically enabling when sensors are costly, and it may also enable faster state estimation for low-latency, high-bandwidth control.\n
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\n \n\n \n \n Jaffe, R. L.; Grover, M.; Venturi, S.; Schwenke, D. W.; Valentini, P.; Schwartzentruber, T. E.; and Panesi, M.\n\n\n \n \n \n \n \n Comparison of potential energy surface and computed rate coefficients for N2 dissociation.\n \n \n \n \n\n\n \n\n\n\n Journal of Thermophysics and Heat Transfer, 32(4): 869–881. September 2018.\n Publisher: American Institute of Aeronautics and Astronautics Inc.\n\n\n\n
\n\n\n\n \n \n \"ComparisonPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{jaffe2018,\n\ttitle = {Comparison of potential energy surface and computed rate coefficients for {N2} dissociation},\n\tvolume = {32},\n\turl = {https://arc.aiaa.org/doi/abs/10.2514/1.T5417},\n\tdoi = {10.2514/1.T5417},\n\tabstract = {Comparisons are made between potential energy surfaces (PESs) for N2 N and N2 N2 collisions and between rate coefficients for N2 dissociation that were computed using the quasi-classical trajectory (QCT) method on these PESs. For N2 N, Laganà’s empirical London–Eyring–Polanyi–Sato surface is compared with one from NASA Ames Research Center based on ab initio quantum chemistry calculations. For N2 N2, two ab initio PESs (from NASA Ames and from the University of Minnesota) are compared. These use different methods for computing the ground state electronic energy for N4 but give similar results. Thermal N2 dissociation rate coefficients, for the 10,000–30,000 K temperature range, have been computed using each PES, and the results are in excellent agreement. Quasi-stationary state (QSS) rate coefficients using both PESs have been computed at these temperatures using the direct molecular simulation method (DMS) of Schwartzentruber and coworkers. The QSS rate coefficients are up to a factor of 5 lower than the thermal ones, and the thermal and QSS values bracket the results of shock-tube experiments. It is concluded that the combination of ab initio quantum chemistry PESs and QCT calculations provides an attractive approach for the determination of accurate high-temperature rate coefficients for use in aerothermodynamics modeling.},\n\tnumber = {4},\n\tjournal = {Journal of Thermophysics and Heat Transfer},\n\tauthor = {Jaffe, Richard L. and Grover, Maninder and Venturi, Simone and Schwenke, David W. and Valentini, Paolo and Schwartzentruber, Thomas E. and Panesi, Marco},\n\tmonth = sep,\n\tyear = {2018},\n\tnote = {Publisher: American Institute of Aeronautics and Astronautics Inc.},\n\tkeywords = {Aerothermodynamics, CFD, Classical Mechanics, Computing, Direct Simulation Monte Carlo, Energy Distribution, NASA Ames Research Center, Schrodinger Equation, Shock Tube, Thermal Nonequilibrium},\n\tpages = {869--881},\n}\n\n\n\n
\n
\n\n\n
\n Comparisons are made between potential energy surfaces (PESs) for N2 N and N2 N2 collisions and between rate coefficients for N2 dissociation that were computed using the quasi-classical trajectory (QCT) method on these PESs. For N2 N, Laganà’s empirical London–Eyring–Polanyi–Sato surface is compared with one from NASA Ames Research Center based on ab initio quantum chemistry calculations. For N2 N2, two ab initio PESs (from NASA Ames and from the University of Minnesota) are compared. These use different methods for computing the ground state electronic energy for N4 but give similar results. Thermal N2 dissociation rate coefficients, for the 10,000–30,000 K temperature range, have been computed using each PES, and the results are in excellent agreement. Quasi-stationary state (QSS) rate coefficients using both PESs have been computed at these temperatures using the direct molecular simulation method (DMS) of Schwartzentruber and coworkers. The QSS rate coefficients are up to a factor of 5 lower than the thermal ones, and the thermal and QSS values bracket the results of shock-tube experiments. It is concluded that the combination of ab initio quantum chemistry PESs and QCT calculations provides an attractive approach for the determination of accurate high-temperature rate coefficients for use in aerothermodynamics modeling.\n
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\n \n\n \n \n Mbagwu, C. C.; and Driscoll, J. F.\n\n\n \n \n \n \n \n An examination of vehicle design tradeoffs and trajectory optimization for trimmed scramjet-powered hypersonic vehicles on ascent.\n \n \n \n \n\n\n \n\n\n\n In 2018. American Institute of Aeronautics and Astronautics Inc, AIAA\n Issue: 210049\n\n\n\n
\n\n\n\n \n \n \"AnPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{mbagwu2018,\n\ttitle = {An examination of vehicle design tradeoffs and trajectory optimization for trimmed scramjet-powered hypersonic vehicles on ascent},\n\tisbn = {978-1-62410-532-6},\n\turl = {https://arc.aiaa.org/doi/abs/10.2514/6.2018-0417},\n\tdoi = {10.2514/6.2018-0417},\n\tabstract = {Several design rules are discussed that can be helpful in optimizing the design and the ascent trajectory of a generic hypersonic vehicle that is powered by a dual-mode ramjet-scramjet engine. The focus is on “vehicle integration” design rules, which differ from the “propulsion-oriented” optimization that has been discussed in certain textbooks. Vehicle-integration rules account for realistic constraints, including the requirement that the vehicle must be trimmed at all points along an ascent trajectory and that additive drag and vehicle stability are considered. A hypersonic waverider does not follow rules for a conventional airplane, where the goal is a large ratio of wing area to frontal area in order to maximize Lift/Drag ratio. Nor does a waverider follow rules for a rocket (where the goal is to maximize the Thrust/Drag ratio, requiring a small ratio of wing area to frontal area). Instead a waverider requires an optimization of both T/D and L/D, which introduces certain challenges. Governing parameters that were varied were: aspect ratio (b/c), engine inlet width (W), root chord length (c), acceleration profiles (a), and flight Mach number (M). The output parameters selected for optimization were thrust-to-drag (T/D) and lift-to-drag (L/D). Trends for auxiliary parameters such as angle-of-attack (α), elevon deflection angle (δ), and equivalence ratio (φ) were examined. A surrogate-based optimization algorithm was applied. The advantages of selecting the largest possible dynamic pressure are discussed. Trajectory optimization was also performed to minimize fuel burn mf and maximize (T/D) along an ascent trajectory.},\n\tpublisher = {American Institute of Aeronautics and Astronautics Inc, AIAA},\n\tauthor = {Mbagwu, Chukwuka C. and Driscoll, James F.},\n\tyear = {2018},\n\tnote = {Issue: 210049},\n}\n\n\n\n
\n
\n\n\n
\n Several design rules are discussed that can be helpful in optimizing the design and the ascent trajectory of a generic hypersonic vehicle that is powered by a dual-mode ramjet-scramjet engine. The focus is on “vehicle integration” design rules, which differ from the “propulsion-oriented” optimization that has been discussed in certain textbooks. Vehicle-integration rules account for realistic constraints, including the requirement that the vehicle must be trimmed at all points along an ascent trajectory and that additive drag and vehicle stability are considered. A hypersonic waverider does not follow rules for a conventional airplane, where the goal is a large ratio of wing area to frontal area in order to maximize Lift/Drag ratio. Nor does a waverider follow rules for a rocket (where the goal is to maximize the Thrust/Drag ratio, requiring a small ratio of wing area to frontal area). Instead a waverider requires an optimization of both T/D and L/D, which introduces certain challenges. Governing parameters that were varied were: aspect ratio (b/c), engine inlet width (W), root chord length (c), acceleration profiles (a), and flight Mach number (M). The output parameters selected for optimization were thrust-to-drag (T/D) and lift-to-drag (L/D). Trends for auxiliary parameters such as angle-of-attack (α), elevon deflection angle (δ), and equivalence ratio (φ) were examined. A surrogate-based optimization algorithm was applied. The advantages of selecting the largest possible dynamic pressure are discussed. Trajectory optimization was also performed to minimize fuel burn mf and maximize (T/D) along an ascent trajectory.\n
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\n \n\n \n \n Eyi, S.; Hanquist, K. M.; and Boyd, I. D.\n\n\n \n \n \n \n Aerothermodynamic Design Optimization of Hypersonic Vehicles.\n \n \n \n\n\n \n\n\n\n In 2018 Multidisciplinary Analysis and Optimization Conference, 2018. AIAA Paper 2018-3108\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n\n\n\n
\n 
@inproceedings{eyi2018b,\n\ttitle = {Aerothermodynamic {Design} {Optimization} of {Hypersonic} {Vehicles}},\n\tdoi = {10.2514/6.2018-3108},\n\tabstract = {The objective of this study is to develop a reliable and efficient design optimization method for hypersonic vehicles focused on aerothermodynamics. Considering the nature of hypersonic flight, a high-fidelity aerothermodynamic analysis code is utilized for the simulation of weakly ionized hypersonic flows in thermo-chemical non-equilibrium. A gradient-based method is implemented for optimization. Bezier or NURBS curves are used to parametrize the geometry or the geometry change. Linear elasticity theory is implemented for mesh deformation. Penalty functions are utilized to prevent undesired geometrical changes. The design objective is to minimize drag without increasing the heat transfer rate and the maximum values of the surface heat flux, temperature and pressure. Design optimizations are performed at different trajectory points of the IRV-2 vehicle. The effects of parametrizations, the number of design variables and freestream conditions on design performance are studied.},\n\tbooktitle = {2018 {Multidisciplinary} {Analysis} and {Optimization} {Conference}},\n\tpublisher = {AIAA Paper 2018-3108},\n\tauthor = {Eyi, Sinan and Hanquist, Kyle M. and Boyd, Iain D.},\n\tyear = {2018},\n\tkeywords = {own},\n}\n\n\n\n
\n
\n\n\n
\n The objective of this study is to develop a reliable and efficient design optimization method for hypersonic vehicles focused on aerothermodynamics. Considering the nature of hypersonic flight, a high-fidelity aerothermodynamic analysis code is utilized for the simulation of weakly ionized hypersonic flows in thermo-chemical non-equilibrium. A gradient-based method is implemented for optimization. Bezier or NURBS curves are used to parametrize the geometry or the geometry change. Linear elasticity theory is implemented for mesh deformation. Penalty functions are utilized to prevent undesired geometrical changes. The design objective is to minimize drag without increasing the heat transfer rate and the maximum values of the surface heat flux, temperature and pressure. Design optimizations are performed at different trajectory points of the IRV-2 vehicle. The effects of parametrizations, the number of design variables and freestream conditions on design performance are studied.\n
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\n \n\n \n \n Campanell, M D\n\n\n \n \n \n \n Alternative model of space-charge-limited thermionic current flow through a plasma.\n \n \n \n\n\n \n\n\n\n Physical Review E, 97: 1–16. 2018.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n\n\n\n
\n 
@article{campanell2018,\n\ttitle = {Alternative model of space-charge-limited thermionic current flow through a plasma},\n\tvolume = {97},\n\tdoi = {10.1103/PhysRevE.97.043207},\n\tabstract = {It is widely assumed that thermionic current flow through a plasma is limited by a "space-charge-limited" (SCL) cathode sheath that consumes the hot cathode's negative bias and accelerates upstream ions into the cathode. Here, we formulate a fundamentally different current-limited mode. In the "inverse" mode, the potentials of both electrodes are above the plasma potential, so that the plasma ions are confined. The bias is consumed by the anode sheath. There is no potential gradient in the neutral plasma region from resistivity or presheath. The inverse cathode sheath pulls some thermoelectrons back to the cathode, thereby limiting the circuit current. Thermoelectrons entering the zero-field plasma region that undergo collisions may also be sent back to the cathode, further attenuating the circuit current. In planar geometry, the plasma density is shown to vary linearly across the electrode gap. A continuum kinetic planar plasma diode simulation model is set up to compare the properties of current modes with classical, conventional SCL, and inverse cathode sheaths. SCL modes can exist only if charge-exchange collisions are turned off in the potential well of the virtual cathode to prevent ion trapping. With the collisions, the current-limited equilibrium must be inverse. Inverse operating modes should therefore be present or possible in many plasma devices that rely on hot cathodes. Evidence from past experiments is discussed. The inverse mode may offer opportunities to minimize sputtering and power consumption that were not previously explored due to the common assumption of SCL sheaths.},\n\tjournal = {Physical Review E},\n\tauthor = {Campanell, M D},\n\tyear = {2018},\n\tkeywords = {doi:10.1103/PhysRevE.97.043207 url:https://doi.org},\n\tpages = {1--16},\n}\n\n\n\n
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\n It is widely assumed that thermionic current flow through a plasma is limited by a \"space-charge-limited\" (SCL) cathode sheath that consumes the hot cathode's negative bias and accelerates upstream ions into the cathode. Here, we formulate a fundamentally different current-limited mode. In the \"inverse\" mode, the potentials of both electrodes are above the plasma potential, so that the plasma ions are confined. The bias is consumed by the anode sheath. There is no potential gradient in the neutral plasma region from resistivity or presheath. The inverse cathode sheath pulls some thermoelectrons back to the cathode, thereby limiting the circuit current. Thermoelectrons entering the zero-field plasma region that undergo collisions may also be sent back to the cathode, further attenuating the circuit current. In planar geometry, the plasma density is shown to vary linearly across the electrode gap. A continuum kinetic planar plasma diode simulation model is set up to compare the properties of current modes with classical, conventional SCL, and inverse cathode sheaths. SCL modes can exist only if charge-exchange collisions are turned off in the potential well of the virtual cathode to prevent ion trapping. With the collisions, the current-limited equilibrium must be inverse. Inverse operating modes should therefore be present or possible in many plasma devices that rely on hot cathodes. Evidence from past experiments is discussed. The inverse mode may offer opportunities to minimize sputtering and power consumption that were not previously explored due to the common assumption of SCL sheaths.\n
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\n \n\n \n \n Andrienko, D A; and Boyd, I D\n\n\n \n \n \n \n State-specific dissociation in O$_{\\textrm{2}}$-O$_{\\textrm{2}}$ collisions by quasiclassical trajectory method.\n \n \n \n\n\n \n\n\n\n Chemical Physics, 491: 74–81. 2017.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{andrienko2017,\n\ttitle = {State-specific dissociation in {O}$_{\\textrm{2}}$-{O}$_{\\textrm{2}}$ collisions by quasiclassical trajectory method},\n\tvolume = {491},\n\tdoi = {10.1016/j.chemphys.2017.05.005},\n\tjournal = {Chemical Physics},\n\tauthor = {Andrienko, D A and Boyd, I D},\n\tyear = {2017},\n\tpages = {74--81},\n}\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n
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\n \n\n \n \n Herrera-Montojo, J.; Fossati, M.; and Minisci, E.\n\n\n \n \n \n \n Shock-conforming mesh generation for aerodynamic analyses at supersonic regimes.\n \n \n \n\n\n \n\n\n\n Computers & Fluids, 157: 276–293. November 2017.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@article{herrera-montojo2017,\n\ttitle = {Shock-conforming mesh generation for aerodynamic analyses at supersonic regimes},\n\tvolume = {157},\n\tdoi = {https://doi.org/10.1016},\n\tjournal = {Computers \\& Fluids},\n\tauthor = {Herrera-Montojo, J. and Fossati, M. and Minisci, E.},\n\tmonth = nov,\n\tyear = {2017},\n\tpages = {276--293},\n}\n\n\n\n
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\n \n\n \n \n Molina, E.; Spode, C.; Annes da Silva, R. G.; Manosalvas-Kjono, D. E.; Nimmagadda, S.; Economon, T. D.; Alonso, J. J.; and Righi, M.\n\n\n \n \n \n \n Hybrid RANS/LES Calculations in SU2.\n \n \n \n\n\n \n\n\n\n In 23rd AIAA Computational Fluid Dynamics Conference, Denver, Colorado, 2017. AIAA Paper 2017-4284\n \n\n\n\n
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@inproceedings{molina2017,\n\taddress = {Denver, Colorado},\n\ttitle = {Hybrid {RANS}/{LES} {Calculations} in {SU2}},\n\tisbn = {978-1-62410-506-7},\n\tdoi = {10.2514/6.2017-4284},\n\tlanguage = {en},\n\turldate = {2023-01-12},\n\tbooktitle = {23rd {AIAA} {Computational} {Fluid} {Dynamics} {Conference}},\n\tpublisher = {AIAA Paper 2017-4284},\n\tauthor = {Molina, Eduardo and Spode, Cleber and Annes da Silva, Roberto G. and Manosalvas-Kjono, David E. and Nimmagadda, Sravya and Economon, Thomas D. and Alonso, Juan J. and Righi, Marcello},\n\tyear = {2017},\n}\n\n\n\n
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\n \n\n \n \n Tulp, J.; and Beck, P.\n\n\n \n \n \n \n Rocket Lab: Liberating the Small Satellite Market.\n \n \n \n\n\n \n\n\n\n In 2017. AIAA\n \n\n\n\n
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@inproceedings{tulp2017,\n\ttitle = {Rocket {Lab}: {Liberating} the {Small} {Satellite} {Market}},\n\tpublisher = {AIAA},\n\tauthor = {Tulp, Jessica and Beck, Peter},\n\tyear = {2017},\n}\n\n\n\n
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\n \n\n \n \n Griffiths, D. J.\n\n\n \n \n \n \n Introduction to Electrodynamics.\n \n \n \n\n\n \n\n\n\n Cambridge University Press, 2017.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@book{griffiths2017,\n\ttitle = {Introduction to {Electrodynamics}},\n\tisbn = {978-1-108-33351-1},\n\tpublisher = {Cambridge University Press},\n\tauthor = {Griffiths, David J.},\n\tyear = {2017},\n}\n\n\n\n
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\n \n\n \n \n Mortari, D.\n\n\n \n \n \n \n \n Least-Squares Solution of Linear Differential Equations.\n \n \n \n \n\n\n \n\n\n\n Mathematics, 5(4): 48. December 2017.\n \n\n\n\n
\n\n\n\n \n \n \"Least-SquaresPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{mortari2017a,\n\ttitle = {Least-{Squares} {Solution} of {Linear} {Differential} {Equations}},\n\tvolume = {5},\n\tcopyright = {http://creativecommons.org/licenses/by/3.0/},\n\tissn = {2227-7390},\n\turl = {https://www.mdpi.com/2227-7390/5/4/48},\n\tdoi = {10.3390/math5040048},\n\tabstract = {This study shows how to obtain least-squares solutions to initial value problems (IVPs), boundary value problems (BVPs), and multi-value problems (MVPs) for nonhomogeneous linear differential equations (DEs) with nonconstant coefficients of any order. However, without loss of generality, the approach has been applied to second-order DEs. The proposed method has two steps. The first step consists of writing a constrained expression, that has the DE constraints embedded. These kind of expressions are given in terms of a new unknown function,     g ( t )    , and they satisfy the constraints, no matter what     g ( t )     is. The second step consists of expressing     g ( t )     as a linear combination of m independent known basis functions. Specifically, orthogonal polynomials are adopted for the basis functions. This choice requires rewriting the DE and the constraints in terms of a new independent variable,     x ∈ [ − 1 , + 1 ]    . The procedure leads to a set of linear equations in terms of the unknown coefficients of the basis functions that are then computed by least-squares. Numerical examples are provided to quantify the solutions’ accuracy for IVPs, BVPs and MVPs. In all the examples provided, the least-squares solution is obtained with machine error accuracy.},\n\tlanguage = {en},\n\tnumber = {4},\n\turldate = {2024-04-24},\n\tjournal = {Mathematics},\n\tauthor = {Mortari, Daniele},\n\tmonth = dec,\n\tyear = {2017},\n\tkeywords = {embedded linear constraints, interpolation, linear least-squares},\n\tpages = {48},\n}\n\n\n\n
\n
\n\n\n
\n This study shows how to obtain least-squares solutions to initial value problems (IVPs), boundary value problems (BVPs), and multi-value problems (MVPs) for nonhomogeneous linear differential equations (DEs) with nonconstant coefficients of any order. However, without loss of generality, the approach has been applied to second-order DEs. The proposed method has two steps. The first step consists of writing a constrained expression, that has the DE constraints embedded. These kind of expressions are given in terms of a new unknown function, g ( t ) , and they satisfy the constraints, no matter what g ( t ) is. The second step consists of expressing g ( t ) as a linear combination of m independent known basis functions. Specifically, orthogonal polynomials are adopted for the basis functions. This choice requires rewriting the DE and the constraints in terms of a new independent variable, x ∈ [ − 1 , + 1 ] . The procedure leads to a set of linear equations in terms of the unknown coefficients of the basis functions that are then computed by least-squares. Numerical examples are provided to quantify the solutions’ accuracy for IVPs, BVPs and MVPs. In all the examples provided, the least-squares solution is obtained with machine error accuracy.\n
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\n \n\n \n \n Mortari, D.\n\n\n \n \n \n \n The theory of connections: Connecting points.\n \n \n \n\n\n \n\n\n\n Mathematics, 5(4). 2017.\n Number: 57\n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{mortari2017,\n\ttitle = {The theory of connections: {Connecting} points},\n\tvolume = {5},\n\tissn = {2227-7390},\n\tdoi = {10.3390/math5040057},\n\tabstract = {This study introduces a procedure to obtain all interpolating functions, y = f ( x ) , subject to linear constraints on the function and its derivatives defined at specified values. The paper first shows how to express these interpolating functions passing through a single point in three distinct ways: linear, additive, and rational. Then, using the additive formalism, interpolating functions with linear constraints on one, two, and n points are introduced as well as those satisfying relative constraints. In particular, for expressions passing through n points, a generalization of the Waring’s interpolation form is introduced. An alternative approach to derive additive constraint interpolating expressions is introduced requiring the inversion of a matrix with dimensions equally the number of constraints. Finally, continuous and discontinuous interpolating periodic functions passing through a set of points with specified periods are provided. This theory has already been applied to obtain least-squares solutions of initial and boundary value problems applied to nonhomogeneous linear differential equations with nonconstant coefficients.},\n\tnumber = {4},\n\tjournal = {Mathematics},\n\tauthor = {Mortari, Daniele},\n\tyear = {2017},\n\tnote = {Number: 57},\n}\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n
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\n This study introduces a procedure to obtain all interpolating functions, y = f ( x ) , subject to linear constraints on the function and its derivatives defined at specified values. The paper first shows how to express these interpolating functions passing through a single point in three distinct ways: linear, additive, and rational. Then, using the additive formalism, interpolating functions with linear constraints on one, two, and n points are introduced as well as those satisfying relative constraints. In particular, for expressions passing through n points, a generalization of the Waring’s interpolation form is introduced. An alternative approach to derive additive constraint interpolating expressions is introduced requiring the inversion of a matrix with dimensions equally the number of constraints. Finally, continuous and discontinuous interpolating periodic functions passing through a set of points with specified periods are provided. This theory has already been applied to obtain least-squares solutions of initial and boundary value problems applied to nonhomogeneous linear differential equations with nonconstant coefficients.\n
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\n \n\n \n \n Li, C.; Zhu, D.; Li, X.; Wang, B.; and Chen, J.\n\n\n \n \n \n \n Thermal–stress analysis on the crack formation of tungsten during fusion relevant transient heat loads.\n \n \n \n\n\n \n\n\n\n Nuclear Materials and Energy, 13: 68–73. December 2017.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{li2017,\n\ttitle = {Thermal–stress analysis on the crack formation of tungsten during fusion relevant transient heat loads},\n\tvolume = {13},\n\tissn = {2352-1791},\n\tdoi = {10.1016/j.nme.2017.06.008},\n\tabstract = {In the future fusion devices, ELMs-induced transient heat flux may lead to the surface cracking of tungsten (W) based plasma-facing materials (PFMs). In theory, the cracking is related to the material fracture toughness and the thermal stress-strain caused by transient heat flux. In this paper, a finite element model was successfully built to realize a theoretical semi infinite space. The temperature and stress-strain distribution as well as evolution of W during a single heating-cooling cycle of transient heat flux were simulated and analyzed. It showed that the generation of plastic deformation during the brittle temperature range between room temperature and DBTT (ductile to brittle transition temperature, ∼400 °C) caused the cracking of W during the cooling phase. The cracking threshold for W under transient heat flux was successfully obtained by finite element analysis, to some extent, in consistent with the similar experimental results. Both the heat flux factors (FHF = P·t0.5) and the maximum surface temperatures at cracking thresholds were almost invariant for the transient heat fluxes with different pulse widths and temporal distributions. This method not only identified the theoretical conclusion but also obtained the detail values for W with actual temperature-dependent properties.},\n\turldate = {2024-04-24},\n\tjournal = {Nuclear Materials and Energy},\n\tauthor = {Li, Changjun and Zhu, Dahuan and Li, Xiangbin and Wang, Baoguo and Chen, Junling},\n\tmonth = dec,\n\tyear = {2017},\n\tkeywords = {Cracking threshold, Finite element analysis, Plasma-facing materials, Tungsten},\n\tpages = {68--73},\n}\n\n\n\n\n\n\n\n
\n
\n\n\n
\n In the future fusion devices, ELMs-induced transient heat flux may lead to the surface cracking of tungsten (W) based plasma-facing materials (PFMs). In theory, the cracking is related to the material fracture toughness and the thermal stress-strain caused by transient heat flux. In this paper, a finite element model was successfully built to realize a theoretical semi infinite space. The temperature and stress-strain distribution as well as evolution of W during a single heating-cooling cycle of transient heat flux were simulated and analyzed. It showed that the generation of plastic deformation during the brittle temperature range between room temperature and DBTT (ductile to brittle transition temperature, ∼400 °C) caused the cracking of W during the cooling phase. The cracking threshold for W under transient heat flux was successfully obtained by finite element analysis, to some extent, in consistent with the similar experimental results. Both the heat flux factors (FHF = P·t0.5) and the maximum surface temperatures at cracking thresholds were almost invariant for the transient heat fluxes with different pulse widths and temporal distributions. This method not only identified the theoretical conclusion but also obtained the detail values for W with actual temperature-dependent properties.\n
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\n \n\n \n \n Hanquist, K. M\n\n\n \n \n \n \n \n Modeling of Electron Transpiration Cooling for Leading Edges of Hypersonic Vehicles.\n \n \n \n \n\n\n \n\n\n\n Ph.D. Thesis, University of Michigan, Ann Arbor, 2017.\n Place: Ann Arbor\n\n\n\n
\n\n\n\n \n \n \"ModelingPaper\n  \n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n\n\n\n
\n 
@phdthesis{hanquist2017a,\n\taddress = {Ann Arbor},\n\ttitle = {Modeling of {Electron} {Transpiration} {Cooling} for {Leading} {Edges} of {Hypersonic} {Vehicles}},\n\turl = {http://hdl.handle.net/2027.42/138537},\n\tschool = {University of Michigan},\n\tauthor = {Hanquist, Kyle M},\n\tyear = {2017},\n\tnote = {Place: Ann Arbor},\n\tkeywords = {etc},\n}\n\n\n\n
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\n \n\n \n \n Scoggins, J.\n\n\n \n \n \n \n \n Development of numerical methods and study of coupled flow, radiation, and ablation phenomena for atmospheric entry.\n \n \n \n \n\n\n \n\n\n\n Ph.D. Thesis, Université Paris Saclay (COmUE), 2017.\n \n\n\n\n
\n\n\n\n \n \n \"DevelopmentPaper\n  \n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@phdthesis{scoggins2017,\n\ttitle = {Development of numerical methods and study of coupled flow, radiation, and ablation phenomena for atmospheric entry},\n\turl = {https://theses.hal.science/tel-01639797},\n\tlanguage = {en},\n\tschool = {Université Paris Saclay (COmUE)},\n\tauthor = {Scoggins, James},\n\tyear = {2017},\n}\n\n\n\n\n\n\n\n
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\n \n\n \n \n Parussini, L.; Venturi, D.; Perdikaris, P.; and Karniadakis, G. E.\n\n\n \n \n \n \n Multi-fidelity Gaussian process regression for prediction of random fields.\n \n \n \n\n\n \n\n\n\n Journal of Computational Physics, 336: 36–50. 2017.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{parussini2017,\n\ttitle = {Multi-fidelity {Gaussian} process regression for prediction of random fields},\n\tvolume = {336},\n\tdoi = {10.1016/j.jcp.2017.01.047},\n\tjournal = {Journal of Computational Physics},\n\tauthor = {Parussini, L. and Venturi, D. and Perdikaris, P. and Karniadakis, G. E.},\n\tyear = {2017},\n\tkeywords = {Gaussian random fields, Multi-fidelity modeling, Recursive co-kriging, Uncertainty quantification},\n\tpages = {36--50},\n}\n\n\n\n
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\n \n\n \n \n Kimmel, R. L.; Borg, M. P.; Jewell, J. S.; Lam, K.; Bowersox, R. D.; Srinivasan, R.; Fuchs, S.; and Mooney, T.\n\n\n \n \n \n \n AFRL Ludwieg Tube Initial Performance.\n \n \n \n\n\n \n\n\n\n In 55th AIAA Aerospace Sciences Meeting, Grapevine, Texas, January 2017. AIAA Paper 2017-0102\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{kimmel2017,\n\taddress = {Grapevine, Texas},\n\ttitle = {{AFRL} {Ludwieg} {Tube} {Initial} {Performance}},\n\tdoi = {10.2514/6.2017-0102},\n\tlanguage = {en},\n\turldate = {2023-08-08},\n\tbooktitle = {55th {AIAA} {Aerospace} {Sciences} {Meeting}},\n\tpublisher = {AIAA Paper 2017-0102},\n\tauthor = {Kimmel, Roger L. and Borg, Matthew P. and Jewell, Joseph S. and Lam, KIng-Yiu and Bowersox, Rodney D. and Srinivasan, Ravi and Fuchs, Steven and Mooney, Thomas},\n\tmonth = jan,\n\tyear = {2017},\n}\n\n\n\n
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\n \n\n \n \n Edwards, L.; and Tumin, A.\n\n\n \n \n \n \n Real gas effects on receptivity to kinetic fluctuations.\n \n \n \n\n\n \n\n\n\n In 55th AIAA Aerospace Sciences Meeting, Grapevine, Texas, January 2017. AIAA Paper 2017-0070\n \n\n\n\n
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\n 
@inproceedings{edwards2017,\n\taddress = {Grapevine, Texas},\n\ttitle = {Real gas effects on receptivity to kinetic fluctuations},\n\tdoi = {10.2514/6.2017-0070},\n\tlanguage = {en},\n\turldate = {2023-08-08},\n\tbooktitle = {55th {AIAA} {Aerospace} {Sciences} {Meeting}},\n\tpublisher = {AIAA Paper 2017-0070},\n\tauthor = {Edwards, Luke and Tumin, Anatoli},\n\tmonth = jan,\n\tyear = {2017},\n}\n\n\n\n\n\n\n\n
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\n \n\n \n \n Zhang, Q.; and He, L.\n\n\n \n \n \n \n \n Turbine blade tip aero-thermal management: Some recent advances and research outlook.\n \n \n \n \n\n\n \n\n\n\n Journal of the Global Power and Propulsion Society. 2017.\n \n\n\n\n
\n\n\n\n \n \n \"TurbinePaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{zhang2017,\n\ttitle = {Turbine blade tip aero-thermal management: {Some} recent advances and research outlook},\n\turl = {https://doi.org/10.22261/JGPPS.K7ADQC},\n\tdoi = {10.22261/JGPPS.K7ADQC},\n\tjournal = {Journal of the Global Power and Propulsion Society},\n\tauthor = {Zhang, Qiang and He, Li},\n\tyear = {2017},\n\tkeywords = {aerodynamics, gas turbine, heat transfer},\n}\n\n\n\n
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\n \n\n \n \n Go, D. B.; Haase, J. R.; George, J.; Mannhart, J.; Wanke, R.; Nojeh, A.; and Nemanich, R.\n\n\n \n \n \n \n Thermionic Energy Conversion in the Twenty-first Century: Advances and Opportunities for Space and Terrestrial Applications.\n \n \n \n\n\n \n\n\n\n Frontiers in Mechanical Engineering. November 2017.\n Publisher: Frontiers\n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{go2017,\n\ttitle = {Thermionic {Energy} {Conversion} in the {Twenty}-first {Century}: {Advances} and {Opportunities} for {Space} and {Terrestrial} {Applications}},\n\tdoi = {10.3389/FMECH.2017.00013},\n\tabstract = {Thermionic energy conversion is the direct conversion of heat into electricity by the mechanism of thermionic emission, the spontaneous ejection of hot electrons from a surface. Although the physical mechanism has been known for over a century, it has yet to be consistently realized in a manner practical for large-scale deployment. This perspective article provides an assessment of the potential of thermionic energy conversion systems for space and terrestrial applications in the 21st century, overviewing recent advances in the field and identifying key research challenges. Recent developments as well as persisting research needs in materials, device design, fundamental understanding, and testing and validation are discussed.},\n\tjournal = {Frontiers in Mechanical Engineering},\n\tauthor = {Go, David B. and Haase, John R. and George, Jeffrey and Mannhart, Jochen and Wanke, Robin and Nojeh, Alireza and Nemanich, Robert},\n\tmonth = nov,\n\tyear = {2017},\n\tnote = {Publisher: Frontiers},\n\tkeywords = {Photo-Enhanced Thermionic Emission, Thermal energy conversion, Thermionic energy conversion, thermionic emission, thermoelectronic energy conversion},\n}\n\n\n\n
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\n Thermionic energy conversion is the direct conversion of heat into electricity by the mechanism of thermionic emission, the spontaneous ejection of hot electrons from a surface. Although the physical mechanism has been known for over a century, it has yet to be consistently realized in a manner practical for large-scale deployment. This perspective article provides an assessment of the potential of thermionic energy conversion systems for space and terrestrial applications in the 21st century, overviewing recent advances in the field and identifying key research challenges. Recent developments as well as persisting research needs in materials, device design, fundamental understanding, and testing and validation are discussed.\n
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\n \n\n \n \n Kazemba, C. D.; Braun, R. D.; Clark, I. G.; and Schoenenberger, M.\n\n\n \n \n \n \n \n Survey of blunt-body supersonic dynamic stability.\n \n \n \n \n\n\n \n\n\n\n Journal of Spacecraft and Rockets, 54(1): 109–127. October 2017.\n Publisher: American Institute of Aeronautics and Astronautics Inc.\n\n\n\n
\n\n\n\n \n \n \"SurveyPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{kazemba2017,\n\ttitle = {Survey of blunt-body supersonic dynamic stability},\n\tvolume = {54},\n\turl = {https://arc.aiaa.org/doi/10.2514/1.A33552},\n\tdoi = {10.2514/1.A33552},\n\tnumber = {1},\n\tjournal = {Journal of Spacecraft and Rockets},\n\tauthor = {Kazemba, Cole D. and Braun, Robert D. and Clark, Ian G. and Schoenenberger, Mark},\n\tmonth = oct,\n\tyear = {2017},\n\tnote = {Publisher: American Institute of Aeronautics and Astronautics Inc.},\n\tkeywords = {Aerodynamic Characteristics, Aerodynamic Performance, Aerospace Engineering, Flow Separation, Hypersonic Inflatable Aerodynamic Decelerator, NASA Langley Research Center, Planetary Exploration, Pressure Coefficient, Supersonic Wind Tunnels, Thermal Protection System},\n\tpages = {109--127},\n}\n\n\n\n
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\n \n\n \n \n Chazot, O.; and Helber, B.\n\n\n \n \n \n \n Plasma Wind Tunnel Testing of Electron Transpiration Cooling Concept.\n \n \n \n\n\n \n\n\n\n Technical Report 2017.\n Issue: AD1028658\n\n\n\n
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@techreport{chazot2017,\n\ttitle = {Plasma {Wind} {Tunnel} {Testing} of {Electron} {Transpiration} {Cooling} {Concept}},\n\tauthor = {Chazot, Olivier and Helber, Bernd},\n\tyear = {2017},\n\tnote = {Issue: AD1028658},\n\tkeywords = {etc},\n}\n\n\n\n
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\n \n\n \n \n Jumper, E. J; and Gordeyev, S.\n\n\n \n \n \n \n Physics and Measurement of Aero-Optical Efects: Past and Present.\n \n \n \n\n\n \n\n\n\n Annual Review of Fluid Mechanics, 49(1): 419–441. 2017.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@article{jumper2017,\n\ttitle = {Physics and {Measurement} of {Aero}-{Optical} {Efects}: {Past} and {Present}},\n\tvolume = {49},\n\tnumber = {1},\n\tjournal = {Annual Review of Fluid Mechanics},\n\tauthor = {Jumper, Eric J and Gordeyev, Stanislav},\n\tyear = {2017},\n\tpages = {419--441},\n}\n\n\n\n
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\n \n\n \n \n Boyd, I. D; and Schwartzentruber, T. E\n\n\n \n \n \n \n Nonequilibrium Gas Dynamics and Molecular Simulation.\n \n \n \n\n\n \n\n\n\n Cambridge University Press, 2017.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@book{boyd2017,\n\ttitle = {Nonequilibrium {Gas} {Dynamics} and {Molecular} {Simulation}},\n\tpublisher = {Cambridge University Press},\n\tauthor = {Boyd, Iain D and Schwartzentruber, Thomas E},\n\tyear = {2017},\n}\n\n\n\n
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\n \n\n \n \n Buffenoir, F.; Pichon, T.; and Barreteau, R.\n\n\n \n \n \n \n IXV Thermal Protection System Post-Flight Preliminary analysis.\n \n \n \n\n\n \n\n\n\n In 2017. \n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@inproceedings{buffenoir2017,\n\ttitle = {{IXV} {Thermal} {Protection} {System} {Post}-{Flight} {Preliminary} analysis},\n\tdoi = {10.13009/EUCASS2017-330},\n\tauthor = {Buffenoir, F. and Pichon, T. and Barreteau, R.},\n\tyear = {2017},\n}\n\n\n\n
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\n \n\n \n \n Estrada, M.; Burnett, M.; Campbell, A. G.; Campbell, P. B.; Denetclaw, W. F.; Gutiérrez, C. G.; Hurtado, S.; John, G. H.; Matsui, J.; McGee, R.; Okpodu, C. M.; Robinson, T. J.; Summers, M. F.; Werner-Washburne, M.; and Zavala, M.\n\n\n \n \n \n \n \n Improving Underrepresented Minority Student Persistence in STEM.\n \n \n \n \n\n\n \n\n\n\n CBE - Life Sciences Education, 15(3). October 2017.\n Publisher: American Society for Cell Biology\n\n\n\n
\n\n\n\n \n \n \"ImprovingPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@article{estrada2017,\n\ttitle = {Improving {Underrepresented} {Minority} {Student} {Persistence} in {STEM}},\n\tvolume = {15},\n\turl = {https://www.lifescied.org/doi/abs/10.1187/cbe.16-01-0038},\n\tdoi = {10.1187/CBE.16-01-0038},\n\tabstract = {Members of the Joint Working Group on Improving Underrepresented Minorities (URMs) Persistence in Science, Technology, Engineering and Mathematics (STEM), utilizing Kurt Lewin’s planned approach to...},\n\tnumber = {3},\n\tjournal = {CBE - Life Sciences Education},\n\tauthor = {Estrada, Mica and Burnett, Myra and Campbell, Andrew G. and Campbell, Patricia B. and Denetclaw, Wilfred F. and Gutiérrez, Carlos G. and Hurtado, Sylvia and John, Gilbert H. and Matsui, John and McGee, Richard and Okpodu, Camellia Moses and Robinson, T. Joan and Summers, Michael F. and Werner-Washburne, Maggie and Zavala, MariaElena},\n\tmonth = oct,\n\tyear = {2017},\n\tnote = {Publisher: American Society for Cell Biology},\n}\n\n\n\n
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\n Members of the Joint Working Group on Improving Underrepresented Minorities (URMs) Persistence in Science, Technology, Engineering and Mathematics (STEM), utilizing Kurt Lewin’s planned approach to...\n
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\n \n\n \n \n Currao, G.; Neely, A.; Robert Buttsworth, D.; and Gai, S.\n\n\n \n \n \n \n \n Hypersonic Fluid-Structure Interaction on a Cantilevered Plate.\n \n \n \n \n\n\n \n\n\n\n In 2017. \n \n\n\n\n
\n\n\n\n \n \n \"HypersonicPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@inproceedings{currao2017,\n\ttitle = {Hypersonic {Fluid}-{Structure} {Interaction} on a {Cantilevered} {Plate}},\n\turl = {https://www.researchgate.net/publication/320087702},\n\tdoi = {10.13009/EUCASS2017-299},\n\tabstract = {This work is a numerical and experimental study of fluid-structure interaction at Mach 5.8. Numerical results from low-and high-fidelity models are shown and compared. Procedures and details of the generation of the numerical mesh are given. The mesh topology shape, irrespective of flow direction, shock position, and sonic line location can lead to non-physical results if not optimised. Orthogonality of the cells to the wall is fundamentally important to reach numerical convergence and reliable results. Under an inviscid point of view, piston theory is confirmed to be an appropriate tool in the evaluation of the inviscid pressure over the plate, as it showed good agreement with the empirical data. Concerning the viscous aspects, the shear stress and heat transfer histories shared the same frequency with the structural, and their spatial distribution present a degree for hysteresis. Finally, the boundary layer height changes not only according to local slope and speed of the wall, but it is a function of the actual structural mode of vibration. Nomenclature Flow Variables: q = Heat flux rate on the plate p = Pressure τ = Shear stress on the plate a = Sound speed St = Stanton number Cf = Skin friction coefficient M = Mach number Structural Variables l = Beam element's length L = Plate length T = Period of oscillation th = Plate's thickness w = Structural displacement θ = Local slope ω = Frequency (= 2πf) E = Young's modulus I = Inertia of the beam cross-section M = Mass matrix K = Stiffness matrix D ̅ = Damping matrix ζ = Damping ratio α,β = Rayleigh coefficients Other Variables x = Coordinate tangent to the wall y = Coordinate normal to the wall t = Time η = Ratio between pressure with 3D effects and 2D pressure Subscripts: w = At the wall S = Structure 1 = 1 st mode 2 = Post-shock conditions or 2 nd mode 3 = 3 rd mode ∞ = Freestream conditions Abbreviations: BL = Boundary layer LE = Leading edge PT1= Pressure transducer near the hinge line PT2= Pressure transducer near the trailing edge PT3= Pressure transducer beneath the plate TE = Trailing edge TUSQ = Wind tunnel at University of Southern Queensland},\n\tauthor = {Currao, Gaetano and Neely, Andrew and Robert Buttsworth, David and Gai, S.},\n\tyear = {2017},\n}\n\n\n\n
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\n This work is a numerical and experimental study of fluid-structure interaction at Mach 5.8. Numerical results from low-and high-fidelity models are shown and compared. Procedures and details of the generation of the numerical mesh are given. The mesh topology shape, irrespective of flow direction, shock position, and sonic line location can lead to non-physical results if not optimised. Orthogonality of the cells to the wall is fundamentally important to reach numerical convergence and reliable results. Under an inviscid point of view, piston theory is confirmed to be an appropriate tool in the evaluation of the inviscid pressure over the plate, as it showed good agreement with the empirical data. Concerning the viscous aspects, the shear stress and heat transfer histories shared the same frequency with the structural, and their spatial distribution present a degree for hysteresis. Finally, the boundary layer height changes not only according to local slope and speed of the wall, but it is a function of the actual structural mode of vibration. Nomenclature Flow Variables: q = Heat flux rate on the plate p = Pressure τ = Shear stress on the plate a = Sound speed St = Stanton number Cf = Skin friction coefficient M = Mach number Structural Variables l = Beam element's length L = Plate length T = Period of oscillation th = Plate's thickness w = Structural displacement θ = Local slope ω = Frequency (= 2πf) E = Young's modulus I = Inertia of the beam cross-section M = Mass matrix K = Stiffness matrix D ̅ = Damping matrix ζ = Damping ratio α,β = Rayleigh coefficients Other Variables x = Coordinate tangent to the wall y = Coordinate normal to the wall t = Time η = Ratio between pressure with 3D effects and 2D pressure Subscripts: w = At the wall S = Structure 1 = 1 st mode 2 = Post-shock conditions or 2 nd mode 3 = 3 rd mode ∞ = Freestream conditions Abbreviations: BL = Boundary layer LE = Leading edge PT1= Pressure transducer near the hinge line PT2= Pressure transducer near the trailing edge PT3= Pressure transducer beneath the plate TE = Trailing edge TUSQ = Wind tunnel at University of Southern Queensland\n
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\n \n\n \n \n Hanquist, K. M.; Alkandry, H.; and Boyd, I. D.\n\n\n \n \n \n \n Evaluation of Computational Modeling of Electron Transpiration Cooling at High Enthalpies.\n \n \n \n\n\n \n\n\n\n Journal of Thermophysics and Heat Transfer, 31(2): 283–293. 2017.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n  \n \n 1 download\n \n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n\n\n\n
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@article{hanquist2017c,\n\ttitle = {Evaluation of {Computational} {Modeling} of {Electron} {Transpiration} {Cooling} at {High} {Enthalpies}},\n\tvolume = {31},\n\tdoi = {10.2514/1.T4932},\n\tabstract = {Amodeling approach for electron transpiration cooling of high-enthalpy flight is evaluated through comparison to a set of experiments performed in a plasma arc tunnel for air and argon. The comparisons include air and argon flow at high enthalpies (27.9 and 11.6 MJ/kg, respectively), with a Mach number of 2.5 to 3. The conversion of the reported enthalpies and Mach numbers to freestream temperatures and velocities is discussed. The numerical approach is described, including implementation of a thermionic emission boundary condition and an electric field model. Also described is the implementation of a finite-rate chemistry model for argon ionization. Materials with different electron emission properties are also investigated, including graphite and tungsten. The comparisons include two different geometries with different leading-edge radii. The numerical results produce a wide range of emitted current due to the uncertainties in freestream conditions and emissive material properties, but they still agree well with the experimental measurements.},\n\tnumber = {2},\n\tjournal = {Journal of Thermophysics and Heat Transfer},\n\tauthor = {Hanquist, Kyle M. and Alkandry, Hicham and Boyd, Iain D.},\n\tyear = {2017},\n\tkeywords = {etc, own},\n\tpages = {283--293},\n}\n\n\n\n
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\n Amodeling approach for electron transpiration cooling of high-enthalpy flight is evaluated through comparison to a set of experiments performed in a plasma arc tunnel for air and argon. The comparisons include air and argon flow at high enthalpies (27.9 and 11.6 MJ/kg, respectively), with a Mach number of 2.5 to 3. The conversion of the reported enthalpies and Mach numbers to freestream temperatures and velocities is discussed. The numerical approach is described, including implementation of a thermionic emission boundary condition and an electric field model. Also described is the implementation of a finite-rate chemistry model for argon ionization. Materials with different electron emission properties are also investigated, including graphite and tungsten. The comparisons include two different geometries with different leading-edge radii. The numerical results produce a wide range of emitted current due to the uncertainties in freestream conditions and emissive material properties, but they still agree well with the experimental measurements.\n
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\n \n\n \n \n Schwartzentruber, T. E; Grover, M S; and Valentini, P.\n\n\n \n \n \n \n Direct Molecular Simulation of Nonequilibrium Dilute Gases.\n \n \n \n\n\n \n\n\n\n Journal of Thermophysics and Heat Transfer, 32(4). 2017.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@article{schwartzentruber2017,\n\ttitle = {Direct {Molecular} {Simulation} of {Nonequilibrium} {Dilute} {Gases}},\n\tvolume = {32},\n\tdoi = {10.2514/1.T5188},\n\tnumber = {4},\n\tjournal = {Journal of Thermophysics and Heat Transfer},\n\tauthor = {Schwartzentruber, Thomas E and Grover, M S and Valentini, Paolo},\n\tyear = {2017},\n}\n\n\n\n
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\n \n\n \n \n Hanquist, K. M.; Hara, K.; and Boyd, I. D.\n\n\n \n \n \n \n Detailed modeling of electron emission for transpiration cooling of hypersonic vehicles.\n \n \n \n\n\n \n\n\n\n Journal of Applied Physics, 121(5): 1–13. 2017.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n  \n \n 2 downloads\n \n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n\n\n\n
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@article{hanquist2017b,\n\ttitle = {Detailed modeling of electron emission for transpiration cooling of hypersonic vehicles},\n\tvolume = {121},\n\tdoi = {10.1063/1.4974961},\n\tnumber = {5},\n\tjournal = {Journal of Applied Physics},\n\tauthor = {Hanquist, Kyle M. and Hara, Kentaro and Boyd, Iain D.},\n\tyear = {2017},\n\tkeywords = {own},\n\tpages = {1--13},\n}\n\n\n\n
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\n \n\n \n \n Viladegut, A.; Düzel, Ü.; and Chazot, O.\n\n\n \n \n \n \n Diffusion effects on the determination of surface catalysis in Inductively Coupled Plasma facility.\n \n \n \n\n\n \n\n\n\n Chemical Physics, 485-486: 88–97. March 2017.\n Publisher: North-Holland\n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
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@article{viladegut2017,\n\ttitle = {Diffusion effects on the determination of surface catalysis in {Inductively} {Coupled} {Plasma} facility},\n\tvolume = {485-486},\n\tdoi = {10.1016/J.CHEMPHYS.2017.02.002},\n\tabstract = {Atomic recombination is an important process to consider when computing the heat flux transferred to the wall of a re-entry vehicle. Two chemical processes are influencing the species diffusion in the boundary layer surrounding a re-usable Thermal Protection System: gas phase reactions and catalytic recombination at the surface. The coupling between them is not normally taken into account when determining the catalytic recombination coefficient (γ) in plasma facilities. This work aims to provide evidence of such coupling based on both a theoretical analysis and an experimental campaign in the VKI-Plasmatron facility. Recombination coefficient measurements at off-stagnation point configuration on a linear copper calorimeter are provided. An evolution from a high-catalytic to a low-catalytic condition due to the boundary layer growth along the probe is observed. This result is consistent with a parametric analysis carried out using the in-house non-equilibrium boundary layer solver, which shows how the experimentally determined catalysis could be influenced by the amount of gas-phase recombination inside the boundary layer.},\n\tjournal = {Chemical Physics},\n\tauthor = {Viladegut, Alan and Düzel, Ümran and Chazot, Olivier},\n\tmonth = mar,\n\tyear = {2017},\n\tnote = {Publisher: North-Holland},\n\tkeywords = {Boundary layer, Chemical reactions, Flat plate, Plasmatron, Wall catalysis},\n\tpages = {88--97},\n}\n\n\n\n
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\n Atomic recombination is an important process to consider when computing the heat flux transferred to the wall of a re-entry vehicle. Two chemical processes are influencing the species diffusion in the boundary layer surrounding a re-usable Thermal Protection System: gas phase reactions and catalytic recombination at the surface. The coupling between them is not normally taken into account when determining the catalytic recombination coefficient (γ) in plasma facilities. This work aims to provide evidence of such coupling based on both a theoretical analysis and an experimental campaign in the VKI-Plasmatron facility. Recombination coefficient measurements at off-stagnation point configuration on a linear copper calorimeter are provided. An evolution from a high-catalytic to a low-catalytic condition due to the boundary layer growth along the probe is observed. This result is consistent with a parametric analysis carried out using the in-house non-equilibrium boundary layer solver, which shows how the experimentally determined catalysis could be influenced by the amount of gas-phase recombination inside the boundary layer.\n
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\n \n\n \n \n Hanquist, K. M.; and Boyd, I. D.\n\n\n \n \n \n \n Computational analysis of electron transpiration cooling for hypersonic vehicles.\n \n \n \n\n\n \n\n\n\n In AIAA SciTech Forum - 55th AIAA Aerospace Sciences Meeting, pages 1–12, 2017. AIAA Paper 2017-0900\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n  \n \n 3 downloads\n \n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n\n\n\n
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@inproceedings{hanquist2017,\n\ttitle = {Computational analysis of electron transpiration cooling for hypersonic vehicles},\n\tdoi = {10.2514/6.2017-0900},\n\tabstract = {Simulations of a leading edge of a hypersonic vehicle using computational fluid dynamics (CFD) and a material response code are presented in order to investigate the effect in-depth surface conduction has on electron transpiration cooling (ETC). ETC is a recently proposed thermal management approach. Previous numerical studies have shown that ETC can significantly lower the stagnation point surface temperature of sharp leading edges of hypersonic vehicles. However, these studies have neglected the effect of heat also being conducted into the material as opposed to only into the flow via radiative cooling and ETC. A modeling approach is presented for ETC, which includes the boundary conditions for electron emission from the surface, accounting for the electric field and space-charge limit effects within the near-wall plasma sheath. A material response code is used to determine typical values of in-depth surface conduction for the test cases studied. Since ETC materials are still being developed, a parametric study is conducted for a range of material properties pertinent to ETC. The results of this study are used to generate in-depth surface conduction profiles, which are implemented into the CFD framework. The CFD simulations show that including in-depth surface conduction results in lower surface temperatures than predicted with radiative and ETC cooling alone. This is because in-depth surface conduction complements radiative cooling and ETC by moving heat away from the surface, in the case of surface conduction by moving the energy into the material, allowing for a lower surface temperature. The results also show that ETC remains a major mode of heat transfer away from the surface, even with in-depth surface conduction. This suggests that ETC is still a promising mode of thermal management, especially since it transfers energy to the flow instead of into the material.},\n\tbooktitle = {{AIAA} {SciTech} {Forum} - 55th {AIAA} {Aerospace} {Sciences} {Meeting}},\n\tpublisher = {AIAA Paper 2017-0900},\n\tauthor = {Hanquist, Kyle M. and Boyd, Iain D.},\n\tyear = {2017},\n\tkeywords = {etc, own, ★},\n\tpages = {1--12},\n}\n\n\n\n
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\n Simulations of a leading edge of a hypersonic vehicle using computational fluid dynamics (CFD) and a material response code are presented in order to investigate the effect in-depth surface conduction has on electron transpiration cooling (ETC). ETC is a recently proposed thermal management approach. Previous numerical studies have shown that ETC can significantly lower the stagnation point surface temperature of sharp leading edges of hypersonic vehicles. However, these studies have neglected the effect of heat also being conducted into the material as opposed to only into the flow via radiative cooling and ETC. A modeling approach is presented for ETC, which includes the boundary conditions for electron emission from the surface, accounting for the electric field and space-charge limit effects within the near-wall plasma sheath. A material response code is used to determine typical values of in-depth surface conduction for the test cases studied. Since ETC materials are still being developed, a parametric study is conducted for a range of material properties pertinent to ETC. The results of this study are used to generate in-depth surface conduction profiles, which are implemented into the CFD framework. The CFD simulations show that including in-depth surface conduction results in lower surface temperatures than predicted with radiative and ETC cooling alone. This is because in-depth surface conduction complements radiative cooling and ETC by moving heat away from the surface, in the case of surface conduction by moving the energy into the material, allowing for a lower surface temperature. The results also show that ETC remains a major mode of heat transfer away from the surface, even with in-depth surface conduction. This suggests that ETC is still a promising mode of thermal management, especially since it transfers energy to the flow instead of into the material.\n
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\n \n\n \n \n Sagerman, D. G; Dasque, N.; Rumpfkeil, M. P; and Hellman, B.\n\n\n \n \n \n \n \n Comparisons of Measured and Modeled Aero-thermal Distributions for Complex Hypersonic Configurations.\n \n \n \n \n\n\n \n\n\n\n In Grapevine, TX, 2017. \n \n\n\n\n
\n\n\n\n \n \n \"ComparisonsPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@inproceedings{sagerman2017,\n\taddress = {Grapevine, TX},\n\ttitle = {Comparisons of {Measured} and {Modeled} {Aero}-thermal {Distributions} for {Complex} {Hypersonic} {Configurations}},\n\turl = {http://arc.aiaa.org},\n\tdoi = {10.2514/6.2017-0264},\n\tabstract = {The ability to quickly and accurately predict the thermal signature of a complex geometry is important in the early design stages for any aircraft. Due to the lack of hypersonic facilities with this capability, a recent effort has been made to quantify the ability of the Mach 6 tunnel at Wright-Patterson Air Force Base (WPAFB) for this task. The Mach 6 High Reynolds Number Facility at WPAFB in Dayton, Ohio, has been non-operational for the past twenty years, but a recent resurgence in the need for hypersonic test facilities has led to the reactivation of the tunnel. With its restoration, the facility is to include new capabilities to assess hypersonic aero-thermodynamic effects on bodies in Mach 6 flow. Using temperature sensitive paint (TSP) and three complex geometries commonly used in the hypersonic community, experimental tests were conducted inside the Mach 6 tunnel to capture the temperature contours and some pressure data for these geometries at various angles of attack. These results were then compared to numerical analyses conducted using the panel code CBAero, the Euler code Cart3D, the coupled Euler/Boundary layer solver UNLATCH, and Navier-Stokes solutions from FUN3D. Due to the experiments in the tunnel never reaching steady state since paint adherence was affected after about 10 seconds in the high-speed flow, the comparison to steady numerical analysis proved difficult. As a result, the capabilities of the Mach 6 tunnel, in terms of having a quantifiable measure between the experimental and numerical temperature distributions, could not be assessed and instead general qualitative comparisons were made. Nomenclature a Speed of sound α or AOA Angle of attack C D Drag coefficient C L Lift coefficient C M Pitching moment coefficient C p Pressure coefficient M Mach number T Temperature [Kelvin] ρ Density},\n\tauthor = {Sagerman, Denton G and Dasque, Nastassja and Rumpfkeil, Markus P and Hellman, Barry},\n\tyear = {2017},\n}\n\n\n\n
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\n The ability to quickly and accurately predict the thermal signature of a complex geometry is important in the early design stages for any aircraft. Due to the lack of hypersonic facilities with this capability, a recent effort has been made to quantify the ability of the Mach 6 tunnel at Wright-Patterson Air Force Base (WPAFB) for this task. The Mach 6 High Reynolds Number Facility at WPAFB in Dayton, Ohio, has been non-operational for the past twenty years, but a recent resurgence in the need for hypersonic test facilities has led to the reactivation of the tunnel. With its restoration, the facility is to include new capabilities to assess hypersonic aero-thermodynamic effects on bodies in Mach 6 flow. Using temperature sensitive paint (TSP) and three complex geometries commonly used in the hypersonic community, experimental tests were conducted inside the Mach 6 tunnel to capture the temperature contours and some pressure data for these geometries at various angles of attack. These results were then compared to numerical analyses conducted using the panel code CBAero, the Euler code Cart3D, the coupled Euler/Boundary layer solver UNLATCH, and Navier-Stokes solutions from FUN3D. Due to the experiments in the tunnel never reaching steady state since paint adherence was affected after about 10 seconds in the high-speed flow, the comparison to steady numerical analysis proved difficult. As a result, the capabilities of the Mach 6 tunnel, in terms of having a quantifiable measure between the experimental and numerical temperature distributions, could not be assessed and instead general qualitative comparisons were made. Nomenclature a Speed of sound α or AOA Angle of attack C D Drag coefficient C L Lift coefficient C M Pitching moment coefficient C p Pressure coefficient M Mach number T Temperature [Kelvin] ρ Density\n
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\n \n\n \n \n Brock, J. M.; Stern, E. C.; and Wilder, M. C.\n\n\n \n \n \n \n \n CFD simulations of the supersonic inflatable aerodynamic decelerator (SIAD) ballistic range tests.\n \n \n \n \n\n\n \n\n\n\n In 2017. AIAA Paper 2017-1437\n \n\n\n\n
\n\n\n\n \n \n \"CFDPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@inproceedings{brock2017,\n\ttitle = {{CFD} simulations of the supersonic inflatable aerodynamic decelerator ({SIAD}) ballistic range tests},\n\tisbn = {978-1-62410-447-3},\n\turl = {https://arc.aiaa.org/doi/10.2514/6.2017-1437},\n\tdoi = {10.2514/6.2017-1437},\n\tabstract = {A series of ballistic range tests were performed on a scaled model of the Supersonic Flight Demonstration Test (SFDT) intended to test the Supersonic Inflatable Aerodynamic Decelerator (SIAD) geometry. The purpose of these experiments were to provide aerodynamic coefficients of the vehicle to aid in mission and vehicle design. The experimental data spans the moderate Mach number range, 3:8-2:0, with a total angle of attack (αT) range, 10°-20°. These conditions are intended to span the Mach-α space for the majority of the SFDT experiment. In an effort to validate the predictive capabilities of Computational Fluid Dynamics (CFD) for free-flight aerodynamic behavior, numerical simulations of the ballistic range experiment are performed using the unstructured finite volume Navier-Stokes solver, US3. D. Comparisons to raw vehicle attitude, and post-processed aerodynamic coefficients are made between simulated results and experimental data. The resulting comparisons for both raw model attitude and derived aerodynamic coefficients show good agreement with experimental results. Additionally, near body pressure field values for each trajectory simulated are investigated. Extracted surface and wake pressure data gives further insights into dynamic/flow coupling leading to a potential mechanism for dynamic instability.},\n\tpublisher = {AIAA Paper 2017-1437},\n\tauthor = {Brock, Joseph M. and Stern, Eric C. and Wilder, Michael C.},\n\tyear = {2017},\n}\n\n\n\n
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\n A series of ballistic range tests were performed on a scaled model of the Supersonic Flight Demonstration Test (SFDT) intended to test the Supersonic Inflatable Aerodynamic Decelerator (SIAD) geometry. The purpose of these experiments were to provide aerodynamic coefficients of the vehicle to aid in mission and vehicle design. The experimental data spans the moderate Mach number range, 3:8-2:0, with a total angle of attack (αT) range, 10°-20°. These conditions are intended to span the Mach-α space for the majority of the SFDT experiment. In an effort to validate the predictive capabilities of Computational Fluid Dynamics (CFD) for free-flight aerodynamic behavior, numerical simulations of the ballistic range experiment are performed using the unstructured finite volume Navier-Stokes solver, US3. D. Comparisons to raw vehicle attitude, and post-processed aerodynamic coefficients are made between simulated results and experimental data. The resulting comparisons for both raw model attitude and derived aerodynamic coefficients show good agreement with experimental results. Additionally, near body pressure field values for each trajectory simulated are investigated. Extracted surface and wake pressure data gives further insights into dynamic/flow coupling leading to a potential mechanism for dynamic instability.\n
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\n \n\n \n \n Neitzel, K. J.; and Hanquist, K. M.\n\n\n \n \n \n \n Aerodynamic optimization of a golf driver using computational fluid dynamics.\n \n \n \n\n\n \n\n\n\n In AIAA SciTech Forum - 55th AIAA Aerospace Sciences Meeting, pages 1–8, 2017. AIAA Paper 2017-0724\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n\n\n\n
\n 
@inproceedings{neitzel2017b,\n\ttitle = {Aerodynamic optimization of a golf driver using computational fluid dynamics},\n\tdoi = {10.2514/6.2017-0724},\n\tabstract = {Driving distance and accuracy are the two key characteristics to an ideal golf drive. Besides having correct swing mechanics, there are numerous approaches that have been advanced to improve driver distance and accuracy, including driver shape, size, and material throughout the history of golf. Currently, with strict equipment conformity regulations from the United States Golf Association (USGA), the shape of the golf driver is greatly bounded, resulting in designs with marked improvements in design performance becoming less common. The required blunt body shape of the golf driver leads itself to be highly affected by aerodynamic forces, specifically pressure and viscous drag. Although the general shape of the golf driver head is greatly defined, small changes in shape can affect the aerodynamics significantly. This paper focusing on using Navier-Stokes computational fluid dynamic (CFD) simulations to reduce the aerodynamic drag while also increasing the yaw stability of the golf driver. Results include a characterization of the flow field experienced during a golf swing as well as the drag analysis of a generic driver. The adjoint method is used to identify surfaces on the driver that are most sensitive to drag. Finally, an optimization approach is discussed to create a low-drag, stable driver with design constraints such as USGA conformity and other parameters important to driver design such as a low center-of-mass and high moment-of-inertia.},\n\tbooktitle = {{AIAA} {SciTech} {Forum} - 55th {AIAA} {Aerospace} {Sciences} {Meeting}},\n\tpublisher = {AIAA Paper 2017-0724},\n\tauthor = {Neitzel, Kevin J. and Hanquist, Kyle M.},\n\tyear = {2017},\n\tkeywords = {own, ★},\n\tpages = {1--8},\n}\n\n\n\n
\n
\n\n\n
\n Driving distance and accuracy are the two key characteristics to an ideal golf drive. Besides having correct swing mechanics, there are numerous approaches that have been advanced to improve driver distance and accuracy, including driver shape, size, and material throughout the history of golf. Currently, with strict equipment conformity regulations from the United States Golf Association (USGA), the shape of the golf driver is greatly bounded, resulting in designs with marked improvements in design performance becoming less common. The required blunt body shape of the golf driver leads itself to be highly affected by aerodynamic forces, specifically pressure and viscous drag. Although the general shape of the golf driver head is greatly defined, small changes in shape can affect the aerodynamics significantly. This paper focusing on using Navier-Stokes computational fluid dynamic (CFD) simulations to reduce the aerodynamic drag while also increasing the yaw stability of the golf driver. Results include a characterization of the flow field experienced during a golf swing as well as the drag analysis of a generic driver. The adjoint method is used to identify surfaces on the driver that are most sensitive to drag. Finally, an optimization approach is discussed to create a low-drag, stable driver with design constraints such as USGA conformity and other parameters important to driver design such as a low center-of-mass and high moment-of-inertia.\n
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\n \n\n \n \n Neitzel, K J; Andrienko, D A; and Boyd, I D\n\n\n \n \n \n \n Aerothermochemical Nonequilibrium Modeling for Oxygen Flows.\n \n \n \n\n\n \n\n\n\n Journal of Thermophysics and Heat Transfer, 31(3): 634–645. 2017.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{neitzel2017c,\n\ttitle = {Aerothermochemical {Nonequilibrium} {Modeling} for {Oxygen} {Flows}},\n\tvolume = {31},\n\tnumber = {3},\n\tjournal = {Journal of Thermophysics and Heat Transfer},\n\tauthor = {Neitzel, K J and Andrienko, D A and Boyd, I D},\n\tyear = {2017},\n\tpages = {634--645},\n}\n\n\n\n
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\n \n\n \n \n Sahai, A.; Lopez, B.; Johnston, C. O.; and Panesi, M.\n\n\n \n \n \n \n Adaptive coarse graining method for energy transfer and dissociation kinetics of polyatomic species.\n \n \n \n\n\n \n\n\n\n The Journal of Chemical Physics, 147(5): 054107–054107. August 2017.\n Publisher: AIP Publishing LLCAIP Publishing\n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
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@article{sahai2017,\n\ttitle = {Adaptive coarse graining method for energy transfer and dissociation kinetics of polyatomic species},\n\tvolume = {147},\n\tdoi = {10.1063/1.4996654},\n\tabstract = {A novel reduced-order method is presented for modeling reacting flows characterized by strong non-equilibrium of the internal energy level distribution of chemical species in the gas. The approach ...},\n\tnumber = {5},\n\tjournal = {The Journal of Chemical Physics},\n\tauthor = {Sahai, A. and Lopez, B. and Johnston, C. O. and Panesi, M.},\n\tmonth = aug,\n\tyear = {2017},\n\tnote = {Publisher: AIP Publishing LLCAIP Publishing},\n\tkeywords = {chemically reactive flow, dissociation, master equation, maximum entropy methods, nitrogen, reduced order systems},\n\tpages = {054107--054107},\n}\n\n\n\n
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\n A novel reduced-order method is presented for modeling reacting flows characterized by strong non-equilibrium of the internal energy level distribution of chemical species in the gas. The approach ...\n
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\n \n\n \n \n Choi, E.; Cho, S.; Lee, D.; Kim, S.; and Hyun Jo, J.\n\n\n \n \n \n \n A Study on Re-entry Predictions of Uncontrolled Space Objects for Space Situational Awareness.\n \n \n \n\n\n \n\n\n\n J. Astron. Space Sci, 34(4): 289–302. 2017.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{choi2017,\n\ttitle = {A {Study} on {Re}-entry {Predictions} of {Uncontrolled} {Space} {Objects} for {Space} {Situational} {Awareness}},\n\tvolume = {34},\n\tdoi = {10.5140/JASS.2017.34.4.289},\n\tabstract = {The key risk analysis technologies for the re-entry of space objects into Earth's atmosphere are divided into four categories: cataloguing and databases of the re-entry of space objects, lifetime and re-entry trajectory predictions, break-up models after re-entry and multiple debris distribution predictions, and ground impact probability models. In this study, we focused on re-entry prediction, including orbital lifetime assessments, for space situational awareness systems. Re-entry predictions are very difficult and are affected by various sources of uncertainty. In particular, during uncontrolled re-entry, large spacecraft may break into several pieces of debris, and the surviving fragments can be a significant hazard for persons and properties on the ground. In recent years, specific methods and procedures have been developed to provide clear information for predicting and analyzing the re-entry of space objects and for ground-risk assessments. Representative tools include object reentry survival analysis tool (ORSAT) and debris assessment software (DAS) developed by National Aeronautics and Space Administration (NASA), spacecraft atmospheric re-entry and aerothermal break-up (SCARAB) and debris risk assessment and mitigation analysis (DRAMA) developed by European Space Agency (ESA), and semi-analytic tool for end of life analysis (STELA) developed by Centre National d'Etudes Spatiales (CNES). In this study, various surveys of existing re-entry space objects are reviewed, and an efficient re-entry prediction technique is suggested based on STELA, the life-cycle analysis tool for satellites, and DRAMA, a re-entry analysis tool. To verify the proposed method, the re-entry of the Tiangong-1 Space Lab, which is expected to re-enter Earth's atmosphere shortly, was simulated. Eventually, these results will provide a basis for space situational awareness risk analyses of the re-entry of space objects.},\n\tnumber = {4},\n\tjournal = {J. Astron. Space Sci},\n\tauthor = {Choi, Eun-Jung and Cho, Sungki and Lee, Deok-Jin and Kim, Siwoo and Hyun Jo, Jung},\n\tyear = {2017},\n\tkeywords = {re-entry prediction, space situational awareness, uncontrolled space objects},\n\tpages = {289--302},\n}\n\n\n\n
\n
\n\n\n
\n The key risk analysis technologies for the re-entry of space objects into Earth's atmosphere are divided into four categories: cataloguing and databases of the re-entry of space objects, lifetime and re-entry trajectory predictions, break-up models after re-entry and multiple debris distribution predictions, and ground impact probability models. In this study, we focused on re-entry prediction, including orbital lifetime assessments, for space situational awareness systems. Re-entry predictions are very difficult and are affected by various sources of uncertainty. In particular, during uncontrolled re-entry, large spacecraft may break into several pieces of debris, and the surviving fragments can be a significant hazard for persons and properties on the ground. In recent years, specific methods and procedures have been developed to provide clear information for predicting and analyzing the re-entry of space objects and for ground-risk assessments. Representative tools include object reentry survival analysis tool (ORSAT) and debris assessment software (DAS) developed by National Aeronautics and Space Administration (NASA), spacecraft atmospheric re-entry and aerothermal break-up (SCARAB) and debris risk assessment and mitigation analysis (DRAMA) developed by European Space Agency (ESA), and semi-analytic tool for end of life analysis (STELA) developed by Centre National d'Etudes Spatiales (CNES). In this study, various surveys of existing re-entry space objects are reviewed, and an efficient re-entry prediction technique is suggested based on STELA, the life-cycle analysis tool for satellites, and DRAMA, a re-entry analysis tool. To verify the proposed method, the re-entry of the Tiangong-1 Space Lab, which is expected to re-enter Earth's atmosphere shortly, was simulated. Eventually, these results will provide a basis for space situational awareness risk analyses of the re-entry of space objects.\n
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\n \n\n \n \n Haack, J. R.; Hauck, C. D.; and Murillo, M. S.\n\n\n \n \n \n \n A Conservative, Entropic Multispecies BGK Model.\n \n \n \n\n\n \n\n\n\n Journal of Statistical Physics, 168(4): 826–856. August 2017.\n Publisher: Springer New York LLC\n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{haack2017,\n\ttitle = {A {Conservative}, {Entropic} {Multispecies} {BGK} {Model}},\n\tvolume = {168},\n\tdoi = {10.1007/S10955-017-1824-9/FIGURES/5},\n\tabstract = {We derive a conservative multispecies BGK model that follows the spirit of the original, single species BGK model by making the specific choice to conserve species masses, total momentum, and total kinetic energy and to satisfy Boltzmann’s H-Theorem. The derivation emphasizes the connection to the Boltzmann operator which allows for direct inclusion of information from higher-fidelity collision physics models. We also develop a complete hydrodynamic closure via the Chapman-Enskog expansion, including a general procedure to generate symmetric diffusion coefficients based on this model. We numerically investigate velocity and temperature relaxation in dense plasmas and compare the model with previous multispecies BGK models and discuss the trade-offs that are made in defining and using them. In particular, we demonstrate that the BGK model in the NRL plasma formulary does not conserve momentum or energy in general.},\n\tnumber = {4},\n\tjournal = {Journal of Statistical Physics},\n\tauthor = {Haack, Jeffrey R. and Hauck, Cory D. and Murillo, Michael S.},\n\tmonth = aug,\n\tyear = {2017},\n\tnote = {Publisher: Springer New York LLC},\n\tkeywords = {BGK, Boltzmann equation, H theorem, Kinetic theory, Multispecies flow, Plasma physics, Transport coefficients},\n\tpages = {826--856},\n}\n\n\n\n
\n
\n\n\n
\n We derive a conservative multispecies BGK model that follows the spirit of the original, single species BGK model by making the specific choice to conserve species masses, total momentum, and total kinetic energy and to satisfy Boltzmann’s H-Theorem. The derivation emphasizes the connection to the Boltzmann operator which allows for direct inclusion of information from higher-fidelity collision physics models. We also develop a complete hydrodynamic closure via the Chapman-Enskog expansion, including a general procedure to generate symmetric diffusion coefficients based on this model. We numerically investigate velocity and temperature relaxation in dense plasmas and compare the model with previous multispecies BGK models and discuss the trade-offs that are made in defining and using them. In particular, we demonstrate that the BGK model in the NRL plasma formulary does not conserve momentum or energy in general.\n
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\n  \n 2016\n \n \n (27)\n \n \n
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\n \n\n \n \n Economon, T. D.; Palacios, F.; Copeland, S. R.; Lukaczyk, T. W.; and Alonso, J. J.\n\n\n \n \n \n \n SU2: An open-source suite for multiphysics simulation and design.\n \n \n \n\n\n \n\n\n\n AIAA Journal, 54(3): 828–846. 2016.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{economon2016,\n\ttitle = {{SU2}: {An} open-source suite for multiphysics simulation and design},\n\tvolume = {54},\n\tdoi = {10.2514/1.J053813},\n\tabstract = {This paper presents the main objectives and a description of the SU2 suite, including the novel software architecture and open-source software engineering strategy. SU2 is a computational analysis and design package that has been developed to solve multiphysics analysis and optimization tasks using unstructured mesh topologies. Its unique architecture iswell suited for extensibility to treat partial-differential-equation-based problems not initially envisioned. The common framework adopted enables the rapid implementation of newphysics packages that can be tightly coupled to form a powerful ensemble of analysis tools to address complex problems facing many engineering communities. The framework is demonstrated on a number, solving both the flow and adjoint systems of equations to provide a highfidelity predictive capability and sensitivity information that can be used for optimal shape design using a gradientbased framework, goal-oriented adaptive mesh refinement, or uncertainty quantification.},\n\tnumber = {3},\n\tjournal = {AIAA Journal},\n\tauthor = {Economon, Thomas D. and Palacios, Francisco and Copeland, Sean R. and Lukaczyk, Trent W. and Alonso, Juan J.},\n\tyear = {2016},\n\tpages = {828--846},\n}\n\n\n\n
\n
\n\n\n
\n This paper presents the main objectives and a description of the SU2 suite, including the novel software architecture and open-source software engineering strategy. SU2 is a computational analysis and design package that has been developed to solve multiphysics analysis and optimization tasks using unstructured mesh topologies. Its unique architecture iswell suited for extensibility to treat partial-differential-equation-based problems not initially envisioned. The common framework adopted enables the rapid implementation of newphysics packages that can be tightly coupled to form a powerful ensemble of analysis tools to address complex problems facing many engineering communities. The framework is demonstrated on a number, solving both the flow and adjoint systems of equations to provide a highfidelity predictive capability and sensitivity information that can be used for optimal shape design using a gradientbased framework, goal-oriented adaptive mesh refinement, or uncertainty quantification.\n
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\n \n\n \n \n Dufrene, A.; MacLean, M.; Holden, M.; Mehta, M.; and Seaford, M.\n\n\n \n \n \n \n \n Space Launch System Base Heating Test: Experimental Operations and Results.\n \n \n \n \n\n\n \n\n\n\n January 2016.\n \n\n\n\n
\n\n\n\n \n \n \"SpacePaper\n  \n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@misc{dufrene2016,\n\ttitle = {Space {Launch} {System} {Base} {Heating} {Test}: {Experimental} {Operations} and {Results}},\n\turl = {https://web.archive.org/web/20190429090136id_/https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20160001817.pdf},\n\tauthor = {Dufrene, Aaron and MacLean, Matthew and Holden, Michael and Mehta, Manish and Seaford, Mark},\n\tmonth = jan,\n\tyear = {2016},\n}\n\n\n\n
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\n \n\n \n \n Wilkinson, M. D.; Dumontier, M.; Aalbersberg, I. J.; Appleton, G.; Axton, M.; Baak, A.; Blomberg, N.; Boiten, J.; da Silva Santos, L. B.; Bourne, P. E.; Bouwman, J.; Brookes, A. J.; Clark, T.; Crosas, M.; Dillo, I.; Dumon, O.; Edmunds, S.; Evelo, C. T.; Finkers, R.; Gonzalez-Beltran, A.; Gray, A. J. G.; Groth, P.; Goble, C.; Grethe, J. S.; Heringa, J.; ’t Hoen, P. A. C.; Hooft, R.; Kuhn, T.; Kok, R.; Kok, J.; Lusher, S. J.; Martone, M. E.; Mons, A.; Packer, A. L.; Persson, B.; Rocca-Serra, P.; Roos, M.; van Schaik, R.; Sansone, S.; Schultes, E.; Sengstag, T.; Slater, T.; Strawn, G.; Swertz, M. A.; Thompson, M.; van der Lei, J.; van Mulligen, E.; Velterop, J.; Waagmeester, A.; Wittenburg, P.; Wolstencroft, K.; Zhao, J.; and Mons, B.\n\n\n \n \n \n \n The FAIR Guiding Principles for scientific data management and stewardship.\n \n \n \n\n\n \n\n\n\n Scientific Data, 3(1): 160018. March 2016.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n  \n \n 3 downloads\n \n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n\n\n\n
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@article{wilkinson2016,\n\ttitle = {The {FAIR} {Guiding} {Principles} for scientific data management and stewardship},\n\tvolume = {3},\n\tcopyright = {2016 The Author(s)},\n\tissn = {2052-4463},\n\tdoi = {10.1038/sdata.2016.18},\n\tabstract = {There is an urgent need to improve the infrastructure supporting the reuse of scholarly data. A diverse set of stakeholders—representing academia, industry, funding agencies, and scholarly publishers—have come together to design and jointly endorse a concise and measureable set of principles that we refer to as the FAIR Data Principles. The intent is that these may act as a guideline for those wishing to enhance the reusability of their data holdings. Distinct from peer initiatives that focus on the human scholar, the FAIR Principles put specific emphasis on enhancing the ability of machines to automatically find and use the data, in addition to supporting its reuse by individuals. This Comment is the first formal publication of the FAIR Principles, and includes the rationale behind them, and some exemplar implementations in the community.},\n\tlanguage = {en},\n\tnumber = {1},\n\turldate = {2024-04-25},\n\tjournal = {Scientific Data},\n\tauthor = {Wilkinson, Mark D. and Dumontier, Michel and Aalbersberg, IJsbrand Jan and Appleton, Gabrielle and Axton, Myles and Baak, Arie and Blomberg, Niklas and Boiten, Jan-Willem and da Silva Santos, Luiz Bonino and Bourne, Philip E. and Bouwman, Jildau and Brookes, Anthony J. and Clark, Tim and Crosas, Mercè and Dillo, Ingrid and Dumon, Olivier and Edmunds, Scott and Evelo, Chris T. and Finkers, Richard and Gonzalez-Beltran, Alejandra and Gray, Alasdair J. G. and Groth, Paul and Goble, Carole and Grethe, Jeffrey S. and Heringa, Jaap and ’t Hoen, Peter A. C. and Hooft, Rob and Kuhn, Tobias and Kok, Ruben and Kok, Joost and Lusher, Scott J. and Martone, Maryann E. and Mons, Albert and Packer, Abel L. and Persson, Bengt and Rocca-Serra, Philippe and Roos, Marco and van Schaik, Rene and Sansone, Susanna-Assunta and Schultes, Erik and Sengstag, Thierry and Slater, Ted and Strawn, George and Swertz, Morris A. and Thompson, Mark and van der Lei, Johan and van Mulligen, Erik and Velterop, Jan and Waagmeester, Andra and Wittenburg, Peter and Wolstencroft, Katherine and Zhao, Jun and Mons, Barend},\n\tmonth = mar,\n\tyear = {2016},\n\tkeywords = {Publication characteristics, Research data},\n\tpages = {160018},\n}\n\n\n\n\n\n\n\n
\n
\n\n\n
\n There is an urgent need to improve the infrastructure supporting the reuse of scholarly data. A diverse set of stakeholders—representing academia, industry, funding agencies, and scholarly publishers—have come together to design and jointly endorse a concise and measureable set of principles that we refer to as the FAIR Data Principles. The intent is that these may act as a guideline for those wishing to enhance the reusability of their data holdings. Distinct from peer initiatives that focus on the human scholar, the FAIR Principles put specific emphasis on enhancing the ability of machines to automatically find and use the data, in addition to supporting its reuse by individuals. This Comment is the first formal publication of the FAIR Principles, and includes the rationale behind them, and some exemplar implementations in the community.\n
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\n \n\n \n \n Hanquist, K. M.; Hara, K.; and Boyd, I. D.\n\n\n \n \n \n \n Modeling of electron transpiration cooling for hypersonic vehicles.\n \n \n \n\n\n \n\n\n\n In 46th AIAA Thermophysics Conference, pages 1–12, 2016. AIAA Paper 2016-4433\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@inproceedings{hanquist2016e,\n\ttitle = {Modeling of electron transpiration cooling for hypersonic vehicles},\n\tdoi = {10.2514/6.2016-4433},\n\tabstract = {Electron transpiration cooling (ETC) is a recently proposed approach to manage the high heating loads experienced at the sharp leading edges of hypersonic vehicles. Computational fluid dynamics can be used to investigate the feasibility of ETC in a hypersonic environment. A modeling approach is presented for ETC, which includes devloping the boundary conditions for electron emission from the surface, accounting for the electric field and space-charge limit effects within the near-wall plasma sheath. Two different analytical models for space-charge limited emission are discussed. The first model assumes that the electrons are emitted cold from the surface while in the second approach the emitted electrons have a finite temperature. The theory shows that emitted electrons with a finite temperature, referred to as warm emission in the present paper, can reach higher levels of emission. This is important because the benefit of ETC, mainly reduction in the surface temperature, is directly correlated to the level of electron emission from the surface. The space-charge limit models are assessed using 1D direct-kinetic plasma sheath simulations. The simulations agree well with the space-charge limit theory proposed by Takamura et al. for emitted electrons with a finite temperature. Both models are implemented into a CFD code, LeMANS, and run for a test case typical of a leading edge radius in a hypersonic flight environment. The CFD results show finite temperature theory results in a larger reduction in wall temperature because more electron emission is allowed for than the cold emission theory. However, even with the electrons being emitted with a finite temperature, the emission still reaches space-charge limits for the test case considered, which can limit the benefits of ETC.},\n\tbooktitle = {46th {AIAA} {Thermophysics} {Conference}},\n\tpublisher = {AIAA Paper 2016-4433},\n\tauthor = {Hanquist, Kyle M. and Hara, Kentaro and Boyd, Iain D.},\n\tyear = {2016},\n\tkeywords = {etc, own, ★},\n\tpages = {1--12},\n}\n\n\n\n
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\n Electron transpiration cooling (ETC) is a recently proposed approach to manage the high heating loads experienced at the sharp leading edges of hypersonic vehicles. Computational fluid dynamics can be used to investigate the feasibility of ETC in a hypersonic environment. A modeling approach is presented for ETC, which includes devloping the boundary conditions for electron emission from the surface, accounting for the electric field and space-charge limit effects within the near-wall plasma sheath. Two different analytical models for space-charge limited emission are discussed. The first model assumes that the electrons are emitted cold from the surface while in the second approach the emitted electrons have a finite temperature. The theory shows that emitted electrons with a finite temperature, referred to as warm emission in the present paper, can reach higher levels of emission. This is important because the benefit of ETC, mainly reduction in the surface temperature, is directly correlated to the level of electron emission from the surface. The space-charge limit models are assessed using 1D direct-kinetic plasma sheath simulations. The simulations agree well with the space-charge limit theory proposed by Takamura et al. for emitted electrons with a finite temperature. Both models are implemented into a CFD code, LeMANS, and run for a test case typical of a leading edge radius in a hypersonic flight environment. The CFD results show finite temperature theory results in a larger reduction in wall temperature because more electron emission is allowed for than the cold emission theory. However, even with the electrons being emitted with a finite temperature, the emission still reaches space-charge limits for the test case considered, which can limit the benefits of ETC.\n
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\n \n\n \n \n Klothakis, A. G.; Nikolos, I. K.; Koehler, T. P.; Gallis, M. A.; and Plimpton, S. J.\n\n\n \n \n \n \n \n Validation simulations of the DSMC code SPARTA.\n \n \n \n \n\n\n \n\n\n\n AIP Conference Proceedings, 1786(1). November 2016.\n Publisher: AIP Publishing LLCAIP Publishing\n\n\n\n
\n\n\n\n \n \n \"ValidationPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{klothakis2016,\n\ttitle = {Validation simulations of the {DSMC} code {SPARTA}},\n\tvolume = {1786},\n\tissn = {9780735414488},\n\turl = {https://aip.scitation.org/doi/abs/10.1063/1.4967566},\n\tdoi = {10.1063/1.4967566},\n\tabstract = {The Direct Simulation Monte Carlo (DSMC) method has been used for over 50 years to simulate rarified gas flows for a wide range of applications where continuum assumptions fail. Extensive efforts t...},\n\tnumber = {1},\n\tjournal = {AIP Conference Proceedings},\n\tauthor = {Klothakis, A. G. and Nikolos, I. K. and Koehler, T. P. and Gallis, M. A. and Plimpton, S. J.},\n\tmonth = nov,\n\tyear = {2016},\n\tnote = {Publisher: AIP Publishing LLCAIP Publishing},\n}\n\n\n\n
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\n The Direct Simulation Monte Carlo (DSMC) method has been used for over 50 years to simulate rarified gas flows for a wide range of applications where continuum assumptions fail. Extensive efforts t...\n
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\n \n\n \n \n Neitzel, K J\n\n\n \n \n \n \n Thermochemical Modeling of Nonequilibrium Oxygen Flows.\n \n \n \n\n\n \n\n\n\n . 2016.\n Place: Ann Arbor\n\n\n\n
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@article{neitzel2016,\n\ttitle = {Thermochemical {Modeling} of {Nonequilibrium} {Oxygen} {Flows}},\n\tauthor = {Neitzel, K J},\n\tyear = {2016},\n\tnote = {Place: Ann Arbor},\n}\n\n\n\n
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\n \n\n \n \n Economon, T. D.; Palacios, F.; Copeland, S. R.; Lukaczyk, T. W.; and Alonso, J. J.\n\n\n \n \n \n \n SU2: An open-source suite for multiphysics simulation and design.\n \n \n \n\n\n \n\n\n\n AIAA Journal, 54(3): 828–846. 2016.\n Publisher: American Institute of Aeronautics and Astronautics Inc.\n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{economon2016a,\n\ttitle = {{SU2}: {An} open-source suite for multiphysics simulation and design},\n\tvolume = {54},\n\tdoi = {10.2514/1.J053813},\n\tabstract = {This paper presents the main objectives and a description of the SU2 suite, including the novel software architecture and open-source software engineering strategy. SU2 is a computational analysis and design package that has been developed to solve multiphysics analysis and optimization tasks using unstructured mesh topologies. Its unique architecture iswell suited for extensibility to treat partial-differential-equation-based problems not initially envisioned. The common framework adopted enables the rapid implementation of newphysics packages that can be tightly coupled to form a powerful ensemble of analysis tools to address complex problems facing many engineering communities. The framework is demonstrated on a number, solving both the flow and adjoint systems of equations to provide a highfidelity predictive capability and sensitivity information that can be used for optimal shape design using a gradientbased framework, goal-oriented adaptive mesh refinement, or uncertainty quantification.},\n\tnumber = {3},\n\tjournal = {AIAA Journal},\n\tauthor = {Economon, Thomas D. and Palacios, Francisco and Copeland, Sean R. and Lukaczyk, Trent W. and Alonso, Juan J.},\n\tyear = {2016},\n\tnote = {Publisher: American Institute of Aeronautics and Astronautics Inc.},\n\tpages = {828--846},\n}\n\n\n\n
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\n This paper presents the main objectives and a description of the SU2 suite, including the novel software architecture and open-source software engineering strategy. SU2 is a computational analysis and design package that has been developed to solve multiphysics analysis and optimization tasks using unstructured mesh topologies. Its unique architecture iswell suited for extensibility to treat partial-differential-equation-based problems not initially envisioned. The common framework adopted enables the rapid implementation of newphysics packages that can be tightly coupled to form a powerful ensemble of analysis tools to address complex problems facing many engineering communities. The framework is demonstrated on a number, solving both the flow and adjoint systems of equations to provide a highfidelity predictive capability and sensitivity information that can be used for optimal shape design using a gradientbased framework, goal-oriented adaptive mesh refinement, or uncertainty quantification.\n
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\n \n\n \n \n Munafò, A.; Venturi, S.; Macdonald, O.; and Panesi, M.\n\n\n \n \n \n \n State-to-state and reduced-order models for dissociation and energy transfer in aerothermal environments.\n \n \n \n\n\n \n\n\n\n In volume 0, 2016. AIAA Paper 2016-0505\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{munafo2016,\n\ttitle = {State-to-state and reduced-order models for dissociation and energy transfer in aerothermal environments},\n\tvolume = {0},\n\tisbn = {978-1-62410-393-3},\n\tdoi = {10.2514/6.2016-0505},\n\tabstract = {This work focuses on the development of State-to-State and reduced-order models for dissociation and energy transfer in aerothermodynamics. The reduction is realized by grouping the population of elementary states into energy bins based on Maxwell-Boltzmann distributions. Different grouping strategies are investigated. Kinetic and thermodynamic data are taken from the rovibrational ab-initio database for the N(4Su)-N2(1Σ+g) system developed at NASA Ames research center. Applications consider the steady expanding flow within the nozzle of the Electric Arc Shock Tube (EAST) facility at NASA Ames Research Center. Numerical solutions are obtained by using a decoupled implicit method. Results show that the population of high-lying vibrational and rotational states depart from the local equilibrium (i.e. Boltzmann distribution). The comparison between the State-to-State and reduced-order model solutions shows that the macroscopic re-combination can be predicted by using only three energy groups.},\n\tpublisher = {AIAA Paper 2016-0505},\n\tauthor = {Munafò, Alessandro and Venturi, Simone and Macdonald, Obyn and Panesi, Marco},\n\tyear = {2016},\n}\n\n\n\n
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\n This work focuses on the development of State-to-State and reduced-order models for dissociation and energy transfer in aerothermodynamics. The reduction is realized by grouping the population of elementary states into energy bins based on Maxwell-Boltzmann distributions. Different grouping strategies are investigated. Kinetic and thermodynamic data are taken from the rovibrational ab-initio database for the N(4Su)-N2(1Σ+g) system developed at NASA Ames research center. Applications consider the steady expanding flow within the nozzle of the Electric Arc Shock Tube (EAST) facility at NASA Ames Research Center. Numerical solutions are obtained by using a decoupled implicit method. Results show that the population of high-lying vibrational and rotational states depart from the local equilibrium (i.e. Boltzmann distribution). The comparison between the State-to-State and reduced-order model solutions shows that the macroscopic re-combination can be predicted by using only three energy groups.\n
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\n \n\n \n \n Andrienko, D A; and Boyd, I D\n\n\n \n \n \n \n Rovibrational energy transfer and dissociation in \\O\\\\textsubscript\\2\\-\\O\\ collisions.\n \n \n \n\n\n \n\n\n\n The Journal of Chemical Physics, 144(10): 1–19. 2016.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{andrienko2016,\n\ttitle = {Rovibrational energy transfer and dissociation in \\{{O}\\}{\\textbackslash}textsubscript\\{2\\}-\\{{O}\\} collisions},\n\tvolume = {144},\n\tnumber = {10},\n\tjournal = {The Journal of Chemical Physics},\n\tauthor = {Andrienko, D A and Boyd, I D},\n\tyear = {2016},\n\tpages = {1--19},\n}\n\n\n\n
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\n \n\n \n \n Vogiatzis, K.; Josyula, E.; and Vedula, P.\n\n\n \n \n \n \n Role of High Fidelity Nonequilibrium Modeling in Laminar and Turbulent Flows for High Speed ISR Missions.\n \n \n \n\n\n \n\n\n\n In Washington, D.C., June 2016. AIAA 2016-4317\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{vogiatzis2016,\n\taddress = {Washington, D.C.},\n\ttitle = {Role of {High} {Fidelity} {Nonequilibrium} {Modeling} in {Laminar} and {Turbulent} {Flows} for {High} {Speed} {ISR} {Missions}},\n\tpublisher = {AIAA 2016-4317},\n\tauthor = {Vogiatzis, Konstantinos and Josyula, Eswar and Vedula, Prakash},\n\tmonth = jun,\n\tyear = {2016},\n}\n\n\n\n
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\n \n\n \n \n Kammara, K. K.; Malaikannan, G.; and Kumar, R.\n\n\n \n \n \n \n \n Molecular Dynamics Study of Gas–Surface Interactions in a Force-Driven Flow of Argon through a Rectangular Nanochannel.\n \n \n \n \n\n\n \n\n\n\n Nanoscale and Microscale Thermophysical Engineering, 20(2): 121–136. April 2016.\n Publisher: Taylor & Francis\n\n\n\n
\n\n\n\n \n \n \"MolecularPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n\n\n\n
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@article{kammara2016,\n\ttitle = {Molecular {Dynamics} {Study} of {Gas}–{Surface} {Interactions} in a {Force}-{Driven} {Flow} of {Argon} through a {Rectangular} {Nanochannel}},\n\tvolume = {20},\n\turl = {https://www.tandfonline.com/doi/abs/10.1080/15567265.2016.1215364},\n\tdoi = {10.1080/15567265.2016.1215364},\n\tabstract = {In recent times, flows through micro- and nanochannels have gained prominence due to their applicability to the fast growing fields of micro- and nanotechnology among others. Understanding gas–surf...},\n\tnumber = {2},\n\tjournal = {Nanoscale and Microscale Thermophysical Engineering},\n\tauthor = {Kammara, Kishore K. and Malaikannan, G. and Kumar, Rakesh},\n\tmonth = apr,\n\tyear = {2016},\n\tnote = {Publisher: Taylor \\& Francis},\n\tkeywords = {Gas-surface interactions, Nano-Poiseuille flow, molecular dynamics method},\n\tpages = {121--136},\n}\n\n\n\n
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\n In recent times, flows through micro- and nanochannels have gained prominence due to their applicability to the fast growing fields of micro- and nanotechnology among others. Understanding gas–surf...\n
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\n \n\n \n \n Santiago Padrón, A.; Alonso, J. J.; and Eldred, M. S.\n\n\n \n \n \n \n \n Multi-fidelity methods in aerodynamic robust optimization.\n \n \n \n \n\n\n \n\n\n\n In 2016. American Institute of Aeronautics and Astronautics Inc, AIAA\n \n\n\n\n
\n\n\n\n \n \n \"Multi-fidelityPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{santiagopadron2016,\n\ttitle = {Multi-fidelity methods in aerodynamic robust optimization},\n\tisbn = {978-1-62410-397-1},\n\turl = {https://arc.aiaa.org/doi/abs/10.2514/6.2016-0680},\n\tdoi = {10.2514/6.2016-0680},\n\tabstract = {In order to design robust and reliable aerospace systems it is necessary to properly quantify the effect of uncertainties on the systems’ behavior. Performing a robust optimization with the highest fidelity method is desired albeit not feasible because of the prohibited computational cost associated with the many simulations needed in the optimization iterations to compute statistics of the system's performance. Here we describe a multi-fidelity method to enable high-fidelity robust optimization. Our multi-fidelity method uses a polynomial chaos expansion constructed from the combination of a low-fidelity model and a model correction to approximate the high-fidelity statistics and the gradients of the statistics used in each optimization iteration. The model correction accounts for the difference between the high-fidelity (Computational Fluid Dynamics RANS) model and the low-fidelity (CFD Euler) model. A key feature of the multi-fidelity method is its incorporation of analytic gradients (adjoints) from the CFD to obtain the gradients of the statistics. The application of the multi-fidelity method to the robust optimization of an RAE2822 airfoil subject to uncertain flow conditions shows that 60\\% to 90\\% computational savings can be achieved when compared to the high-fidelity optimization.},\n\tpublisher = {American Institute of Aeronautics and Astronautics Inc, AIAA},\n\tauthor = {Santiago Padrón, A. and Alonso, Juan J. and Eldred, Michael S.},\n\tyear = {2016},\n}\n\n\n\n
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\n In order to design robust and reliable aerospace systems it is necessary to properly quantify the effect of uncertainties on the systems’ behavior. Performing a robust optimization with the highest fidelity method is desired albeit not feasible because of the prohibited computational cost associated with the many simulations needed in the optimization iterations to compute statistics of the system's performance. Here we describe a multi-fidelity method to enable high-fidelity robust optimization. Our multi-fidelity method uses a polynomial chaos expansion constructed from the combination of a low-fidelity model and a model correction to approximate the high-fidelity statistics and the gradients of the statistics used in each optimization iteration. The model correction accounts for the difference between the high-fidelity (Computational Fluid Dynamics RANS) model and the low-fidelity (CFD Euler) model. A key feature of the multi-fidelity method is its incorporation of analytic gradients (adjoints) from the CFD to obtain the gradients of the statistics. The application of the multi-fidelity method to the robust optimization of an RAE2822 airfoil subject to uncertain flow conditions shows that 60% to 90% computational savings can be achieved when compared to the high-fidelity optimization.\n
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\n \n\n \n \n Tumuklu, O.; Levin, D. A.; Gimelshein, S. F.; and Austin, J. M.\n\n\n \n \n \n \n \n Modeling of near-continuum laminar boundary layer shocks using DSMC.\n \n \n \n \n\n\n \n\n\n\n AIP Conference Proceedings, 1786(1): 050004–050004. November 2016.\n Publisher: AIP Publishing LLCAIP Publishing\n\n\n\n
\n\n\n\n \n \n \"ModelingPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{tumuklu2016,\n\ttitle = {Modeling of near-continuum laminar boundary layer shocks using {DSMC}},\n\tvolume = {1786},\n\tissn = {9780735414488},\n\turl = {https://aip.scitation.org/doi/abs/10.1063/1.4967554},\n\tdoi = {10.1063/1.4967554},\n\tabstract = {The hypersonic flow of nitrogen gas over a double wedge was simulated by the DSMC method using two-dimensional and three-dimensional geometries. The numerical results were compared with experiments...},\n\tnumber = {1},\n\tjournal = {AIP Conference Proceedings},\n\tauthor = {Tumuklu, Ozgur and Levin, Deborah A. and Gimelshein, Sergey F. and Austin, Joanna M.},\n\tmonth = nov,\n\tyear = {2016},\n\tnote = {Publisher: AIP Publishing LLCAIP Publishing},\n\tkeywords = {DSMC, Hypersonic separated flows, Shock-wave boundary layer interactions},\n\tpages = {050004--050004},\n}\n\n\n\n
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\n The hypersonic flow of nitrogen gas over a double wedge was simulated by the DSMC method using two-dimensional and three-dimensional geometries. The numerical results were compared with experiments...\n
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\n \n\n \n \n Alonso, J.; Economon, T.; and Menier, V.\n\n\n \n \n \n \n Mesh Adaptation for SU2 with the INRIA AMG Library.\n \n \n \n\n\n \n\n\n\n In 1st Annual SU2 Developers Meeting, 2016. \n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{alonso2016a,\n\ttitle = {Mesh {Adaptation} for {SU2} with the {INRIA} {AMG} {Library}},\n\tbooktitle = {1st {Annual} {SU2} {Developers} {Meeting}},\n\tauthor = {Alonso, J. and Economon, T. and Menier, V.},\n\tyear = {2016},\n}\n\n\n\n
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\n \n\n \n \n Alonso, J.; Economon, T.; and Menier, V.\n\n\n \n \n \n \n Mesh Adaptation for SU2 with the INRIA AMG Library.\n \n \n \n\n\n \n\n\n\n In 2016. \n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{alonso2016,\n\ttitle = {Mesh {Adaptation} for {SU2} with the {INRIA} {AMG} {Library}},\n\tauthor = {Alonso, J. and Economon, T. and Menier, V.},\n\tyear = {2016},\n}\n\n\n\n
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\n \n\n \n \n Owen, K G; Davidson, D F; and Hanson, R K\n\n\n \n \n \n \n Measurements of Oxygen Dissociation Using Laser Absorption.\n \n \n \n\n\n \n\n\n\n Journal of Thermophysics and Heat Transfer, 30(2). 2016.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{owen2016,\n\ttitle = {Measurements of {Oxygen} {Dissociation} {Using} {Laser} {Absorption}},\n\tvolume = {30},\n\tnumber = {2},\n\tjournal = {Journal of Thermophysics and Heat Transfer},\n\tauthor = {Owen, K G and Davidson, D F and Hanson, R K},\n\tyear = {2016},\n}\n\n\n\n
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\n \n\n \n \n Hanquist, K. M.; and Boyd, I. D.\n\n\n \n \n \n \n Limits for thermionic emission from leading edges of hypersonic vehicles.\n \n \n \n\n\n \n\n\n\n In 54th AIAA Aerospace Sciences Meeting, pages 1–15, 2016. AIAA Paper 2016-0507\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@inproceedings{hanquist2016d,\n\ttitle = {Limits for thermionic emission from leading edges of hypersonic vehicles},\n\tdoi = {10.2514/6.2016-0507},\n\tabstract = {Simulations of electron transpiration cooling (ETC) on the leading edge of a hypersonic vehicle using computational fluid dynamics (CFD) are presented. The thermionic emission boundary condition and electric field model including forced diffusion are discussed. Different analytical models are used to describe the plasma sheath physics in order to avoid resolving the sheath in the computational domain. The first analytical model does not account for emission in the sheath model, so the emission is only limited by the surface temperature. The second approach models the emissive surface as electronically floated, which greatly limits the emission. The last analytical approach biases the emissive surface, which makes it possible to overcome space-charge limits. Each approach is compared and a parametric study is performed to understand the effects that the material work function, freestream velocity, and leading edge geometry has on the ETC effect. The numerical results reveal that modeling the sheath as a floated surface results in the emission, and thus ETC benefits, being greatly limited. However, if the surface is negatively biased, the results show that the emission can overcome space-charge limits and achieve the ideal ETC benefits predicted by temperature limited emission. The study also shows that, along with negatively biasing the surface, emission is enhanced by increasing the number of electrons in the external flowfield by increasing the freestream velocity.},\n\tbooktitle = {54th {AIAA} {Aerospace} {Sciences} {Meeting}},\n\tpublisher = {AIAA Paper 2016-0507},\n\tauthor = {Hanquist, Kyle M. and Boyd, Iain D.},\n\tyear = {2016},\n\tkeywords = {etc, own, ★},\n\tpages = {1--15},\n}\n\n\n\n
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\n Simulations of electron transpiration cooling (ETC) on the leading edge of a hypersonic vehicle using computational fluid dynamics (CFD) are presented. The thermionic emission boundary condition and electric field model including forced diffusion are discussed. Different analytical models are used to describe the plasma sheath physics in order to avoid resolving the sheath in the computational domain. The first analytical model does not account for emission in the sheath model, so the emission is only limited by the surface temperature. The second approach models the emissive surface as electronically floated, which greatly limits the emission. The last analytical approach biases the emissive surface, which makes it possible to overcome space-charge limits. Each approach is compared and a parametric study is performed to understand the effects that the material work function, freestream velocity, and leading edge geometry has on the ETC effect. The numerical results reveal that modeling the sheath as a floated surface results in the emission, and thus ETC benefits, being greatly limited. However, if the surface is negatively biased, the results show that the emission can overcome space-charge limits and achieve the ideal ETC benefits predicted by temperature limited emission. The study also shows that, along with negatively biasing the surface, emission is enhanced by increasing the number of electrons in the external flowfield by increasing the freestream velocity.\n
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\n \n\n \n \n Sellier, M.\n\n\n \n \n \n \n Inverse problems in free surface flows: a review.\n \n \n \n\n\n \n\n\n\n Acta Mech, 227: 913–935. 2016.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{sellier2016,\n\ttitle = {Inverse problems in free surface flows: a review},\n\tvolume = {227},\n\tdoi = {10.1007/s00707-015-1477-1},\n\tabstract = {Free surface flows occur frequently in our daily lives and many natural or industrial settings. Our understanding of such flows has grown tremendously with progress in mathematical modelling and numerical simulations. As a consequence, the response of a free surface to an external perturbation can often be computed and quantified. The free surface response is characteristic of the imposed perturbation and can be thought of as the signature of this perturbation. In this review paper, we survey the literature which deals with the inverse problem of identifying unknown flow conditions or fluid properties from an observed response of the free surface.},\n\tjournal = {Acta Mech},\n\tauthor = {Sellier, Mathieu},\n\tyear = {2016},\n\tpages = {913--935},\n}\n\n\n\n
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\n Free surface flows occur frequently in our daily lives and many natural or industrial settings. Our understanding of such flows has grown tremendously with progress in mathematical modelling and numerical simulations. As a consequence, the response of a free surface to an external perturbation can often be computed and quantified. The free surface response is characteristic of the imposed perturbation and can be thought of as the signature of this perturbation. In this review paper, we survey the literature which deals with the inverse problem of identifying unknown flow conditions or fluid properties from an observed response of the free surface.\n
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\n \n\n \n \n Ward, J.; Harwood, C. M; and Young, Y. L.\n\n\n \n \n \n \n \n Inverse Method for Determination of the In Situ Hydrodynamic Load Distribution in Multi-Phase Flow.\n \n \n \n \n\n\n \n\n\n\n In 2016. \n \n\n\n\n
\n\n\n\n \n \n \"InversePaper\n  \n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{ward2016,\n\ttitle = {Inverse {Method} for {Determination} of the {In} {Situ} {Hydrodynamic} {Load} {Distribution} in {Multi}-{Phase} {Flow}},\n\turl = {https://www.researchgate.net/publication/308627046},\n\tauthor = {Ward, Jacob and Harwood, Casey M and Young, Yin Lu},\n\tyear = {2016},\n}\n\n\n\n
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\n \n\n \n \n Zhang, C.; Shen, G.; Li, C.; Ge, W.; and Li, J.\n\n\n \n \n \n \n \n Hard-sphere/pseudo-particle modelling (HS-PPM) for efficient and scalable molecular simulation of dilute gaseous flow and transport.\n \n \n \n \n\n\n \n\n\n\n Molecular Simulation, 42(14): 1171–1182. September 2016.\n Publisher: Taylor & Francis\n\n\n\n
\n\n\n\n \n \n \"Hard-sphere/pseudo-particlePaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
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@article{zhang2016,\n\ttitle = {Hard-sphere/pseudo-particle modelling ({HS}-{PPM}) for efficient and scalable molecular simulation of dilute gaseous flow and transport},\n\tvolume = {42},\n\turl = {https://www.tandfonline.com/doi/abs/10.1080/08927022.2016.1154551},\n\tdoi = {10.1080/08927022.2016.1154551},\n\tabstract = {Continuum methods are not accurate enough for flows at high Knudsen numbers, whereas rigorous molecular dynamics (MD) methods are too costly for simulations at practical dimensions. Hard-sphere (HS...},\n\tnumber = {14},\n\tjournal = {Molecular Simulation},\n\tauthor = {Zhang, Chenglong and Shen, Guofei and Li, Chengxiang and Ge, Wei and Li, Jinghai},\n\tmonth = sep,\n\tyear = {2016},\n\tnote = {Publisher: Taylor \\& Francis},\n\tkeywords = {Dilute gas, hard-sphere, high Knudsen number, micro chemical engineering, micro-flow, molecular dynamics simulation, pseudo-particle modelling},\n\tpages = {1171--1182},\n}\n\n\n\n
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\n Continuum methods are not accurate enough for flows at high Knudsen numbers, whereas rigorous molecular dynamics (MD) methods are too costly for simulations at practical dimensions. Hard-sphere (HS...\n
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\n \n\n \n \n Albring, T.; Sagebaum, M.; and Gauger, N. R\n\n\n \n \n \n \n Efficient Aerodynamic Design using the Discrete Adjoint Method in SU2.\n \n \n \n\n\n \n\n\n\n In 2016. AIAA 2016-3518\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n  \n \n 1 download\n \n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@inproceedings{albring2016,\n\ttitle = {Efficient {Aerodynamic} {Design} using the {Discrete} {Adjoint} {Method} in {SU2}},\n\tdoi = {10.2514/6.2016-3518},\n\tpublisher = {AIAA 2016-3518},\n\tauthor = {Albring, Tim and Sagebaum, Max and Gauger, Nicolas R},\n\tyear = {2016},\n}\n\n\n\n
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\n \n\n \n \n Brouwer, K. R; Gogulapati, A.; and Mcnamara, J. J\n\n\n \n \n \n \n Efficient Treatment of Structural Deformation for Aerothermoelastic Loads Prediction in High-Speed Flows.\n \n \n \n\n\n \n\n\n\n In San Diego, CA, 2016. \n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@inproceedings{brouwer2016,\n\taddress = {San Diego, CA},\n\ttitle = {Efficient {Treatment} of {Structural} {Deformation} for {Aerothermoelastic} {Loads} {Prediction} in {High}-{Speed} {Flows}},\n\tdoi = {10.2514/6.2016-1089},\n\tabstract = {Accurate and efficient prediction of aerodynamic loads for lightweight aerospace systems is critical to the development of modern reusable high-speed platforms. This is particularly challenging to achieve for structures that exhibit higher order local deformations which, when coupled with invsicid-viscous interactions and non-isentropic flow, can lead to significant local variations in the aerodynamic loads. This study is focused on comparing two strategies for computing aerodynamic pressure loads in order to identify an accurate and efficient approach that requires minimal a priori assumptions regarding the structural response. The first strategy relies on parameterization of the structure in terms of a set of characteristic shapes. The characteristic shapes are identified by exciting the structure of interest using a representative load and then extracting the dominant features of the response. The set of characteristic shapes are then used to generate fluid loads from a Reynold's Averaged Navier-Stokes solution. The second strategy relies on approximate fluid models to compute the aerodynamic pressure. The approximate models considered as part of this study include classical piston theory, a local piston theory method where relevant freestream parameters are replaced by spatially local quantities , and an inviscid-viscous interaction model that attempts to account for the presence of the viscous boundary layer over a deformed surface. The various approaches are compared against Reynold's Averaged Navier-Stokes solutions in the context of a two-dimensional compliant panel subject to shock impingement. The results of this study indicate the following: 1) Accurate and efficient parameteriza-tion of the structure using characteristic shapes is possible, assuming that representative loads are used to excite the structure, 2) The pressure is relatively insensitive to reconstruction errors of structural displacements fit to a truncated set of modes, and 3) Approximate fluid models are capable of reasonably accurate and efficient prediction of pressure loads for a compliant panel subject to shock impingement. Nomenclature A Amplitude a Speed of sound C Covariance matrix C f Coefficient of skin friction c Constant D Flexural stiffness E Young's Modulus f Frequency H Boundary layer shape factor h Panel thickness L Panel length M Mach number m Total number of nodes in each snapshot N Total number of snapshots P Fluid pressure P N oise White noise pressure load},\n\tauthor = {Brouwer, Kirk R and Gogulapati, Abhijit and Mcnamara, Jack J},\n\tyear = {2016},\n}\n\n\n\n
\n
\n\n\n
\n Accurate and efficient prediction of aerodynamic loads for lightweight aerospace systems is critical to the development of modern reusable high-speed platforms. This is particularly challenging to achieve for structures that exhibit higher order local deformations which, when coupled with invsicid-viscous interactions and non-isentropic flow, can lead to significant local variations in the aerodynamic loads. This study is focused on comparing two strategies for computing aerodynamic pressure loads in order to identify an accurate and efficient approach that requires minimal a priori assumptions regarding the structural response. The first strategy relies on parameterization of the structure in terms of a set of characteristic shapes. The characteristic shapes are identified by exciting the structure of interest using a representative load and then extracting the dominant features of the response. The set of characteristic shapes are then used to generate fluid loads from a Reynold's Averaged Navier-Stokes solution. The second strategy relies on approximate fluid models to compute the aerodynamic pressure. The approximate models considered as part of this study include classical piston theory, a local piston theory method where relevant freestream parameters are replaced by spatially local quantities , and an inviscid-viscous interaction model that attempts to account for the presence of the viscous boundary layer over a deformed surface. The various approaches are compared against Reynold's Averaged Navier-Stokes solutions in the context of a two-dimensional compliant panel subject to shock impingement. The results of this study indicate the following: 1) Accurate and efficient parameteriza-tion of the structure using characteristic shapes is possible, assuming that representative loads are used to excite the structure, 2) The pressure is relatively insensitive to reconstruction errors of structural displacements fit to a truncated set of modes, and 3) Approximate fluid models are capable of reasonably accurate and efficient prediction of pressure loads for a compliant panel subject to shock impingement. Nomenclature A Amplitude a Speed of sound C Covariance matrix C f Coefficient of skin friction c Constant D Flexural stiffness E Young's Modulus f Frequency H Boundary layer shape factor h Panel thickness L Panel length M Mach number m Total number of nodes in each snapshot N Total number of snapshots P Fluid pressure P N oise White noise pressure load\n
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\n \n\n \n \n Sanchez, R.; Kline, H.; Thomas, D.; Variyar, A.; Righi, M.; Economon, T.; Alonso, J.; Palacios, R.; Dimitridiadis, G.; and Terrapon, V.\n\n\n \n \n \n \n Assessment of the fluid-structure interaction capabilities for aeronautical applications of the open-source solver SU2.\n \n \n \n\n\n \n\n\n\n In 2016. \n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n  \n \n 2 downloads\n \n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@inproceedings{sanchez2016,\n\ttitle = {Assessment of the fluid-structure interaction capabilities for aeronautical applications of the open-source solver {SU2}},\n\tauthor = {Sanchez, R. and Kline, H. and Thomas, D. and Variyar, A. and Righi, M. and Economon, T. and Alonso, J. and Palacios, R. and Dimitridiadis, G. and Terrapon, V.},\n\tyear = {2016},\n}\n\n\n\n
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\n \n\n \n \n Lemal, A.; Jacobs, C. M.; Perrin, M.; Laux, C. O.; Tran, P.; and Raynaud, E.\n\n\n \n \n \n \n \n Air Collisional-Radiative Modeling with Heavy-Particle Impact Excitation Processes.\n \n \n \n \n\n\n \n\n\n\n Journal of Thermophysics and Heat Transfer, 30(1): 226–239. February 2016.\n Publisher: American Institute of Aeronautics and Astronautics\n\n\n\n
\n\n\n\n \n \n \"AirPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
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@article{lemal2016,\n\ttitle = {Air {Collisional}-{Radiative} {Modeling} with {Heavy}-{Particle} {Impact} {Excitation} {Processes}},\n\tvolume = {30},\n\turl = {https://arc.aiaa.org/doi/abs/10.2514/1.T4549},\n\tdoi = {10.2514/1.T4549},\n\tabstract = {This paper reviews the electron- and heavy-particle impact processes governing the population/depletion of the states of N, O, N2, and N2+, which can be significantly affected by nonequilibrium con...},\n\tnumber = {1},\n\tjournal = {Journal of Thermophysics and Heat Transfer},\n\tauthor = {Lemal, A. and Jacobs, C. M. and Perrin, M.-Y. and Laux, C. O. and Tran, P. and Raynaud, E.},\n\tmonth = feb,\n\tyear = {2016},\n\tnote = {Publisher: American Institute of Aeronautics and Astronautics},\n\tkeywords = {Air Flowing, Boltzmann Constant, Earth, Earth Atmosphere, Einstein Coefficients, Electron Temperature, Franck Condon Principle, Radiative Heating, Shock Layers, Shock Tube},\n\tpages = {226--239},\n}\n\n\n\n
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\n This paper reviews the electron- and heavy-particle impact processes governing the population/depletion of the states of N, O, N2, and N2+, which can be significantly affected by nonequilibrium con...\n
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\n \n\n \n \n Air Force Studies Board\n\n\n \n \n \n \n A Threat to America's Global Vigilance, Reach, and Power: High-Speed Maneuvering Weapons.\n \n \n \n\n\n \n\n\n\n Technical Report 2016.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@techreport{airforcestudiesboard2016,\n\ttitle = {A {Threat} to {America}'s {Global} {Vigilance}, {Reach}, and {Power}: {High}-{Speed} {Maneuvering} {Weapons}},\n\tauthor = {{Air Force Studies Board}},\n\tyear = {2016},\n}\n\n\n\n
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\n \n\n \n \n Parish, E. J.; and Duraisamy, K.\n\n\n \n \n \n \n A paradigm for data-driven predictive modeling using field inversion and machine learning.\n \n \n \n\n\n \n\n\n\n Journal of Computational Physics, 305: 758–774. 2016.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n\n\n\n
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@article{parish2016,\n\ttitle = {A paradigm for data-driven predictive modeling using field inversion and machine learning},\n\tvolume = {305},\n\tdoi = {10.1016/j.jcp.2015.11.012},\n\tabstract = {We propose a modeling paradigm, termed field inversion and machine learning (FIML), that seeks to comprehensively harness data from sources such as high-fidelity simulations and experiments to aid the creation of improved closure models for computational physics applications. In contrast to inferring model parameters, this work uses inverse modeling to obtain corrective, spatially distributed functional terms, offering a route to directly address model-form errors. Once the inference has been performed over a number of problems that are representative of the deficient physics in the closure model, machine learning techniques are used to reconstruct the model corrections in terms of variables that appear in the closure model. These reconstructed functional forms are then used to augment the closure model in a predictive computational setting. As a first demonstrative example, a scalar ordinary differential equation is considered, wherein the model equation has missing and deficient terms. Following this, the methodology is extended to the prediction of turbulent channel flow. In both of these applications, the approach is demonstrated to be able to successfully reconstruct functional corrections and yield accurate predictive solutions while providing a measure of model form uncertainties.},\n\tjournal = {Journal of Computational Physics},\n\tauthor = {Parish, Eric J. and Duraisamy, Karthik},\n\tyear = {2016},\n\tkeywords = {Closure modeling, Data-driven modeling, Machine learning},\n\tpages = {758--774},\n}\n\n\n\n
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\n We propose a modeling paradigm, termed field inversion and machine learning (FIML), that seeks to comprehensively harness data from sources such as high-fidelity simulations and experiments to aid the creation of improved closure models for computational physics applications. In contrast to inferring model parameters, this work uses inverse modeling to obtain corrective, spatially distributed functional terms, offering a route to directly address model-form errors. Once the inference has been performed over a number of problems that are representative of the deficient physics in the closure model, machine learning techniques are used to reconstruct the model corrections in terms of variables that appear in the closure model. These reconstructed functional forms are then used to augment the closure model in a predictive computational setting. As a first demonstrative example, a scalar ordinary differential equation is considered, wherein the model equation has missing and deficient terms. Following this, the methodology is extended to the prediction of turbulent channel flow. In both of these applications, the approach is demonstrated to be able to successfully reconstruct functional corrections and yield accurate predictive solutions while providing a measure of model form uncertainties.\n
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\n \n\n \n \n Alauzet, F.; and Loseille, A.\n\n\n \n \n \n \n A decade of progress on anisotropic mesh adaptation for computational fluid dynamics.\n \n \n \n\n\n \n\n\n\n 23rd International Meshing Roundtable Special Issue: Advances in Mesh Generation, 72: 13–39. March 2016.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
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@article{alauzet2016,\n\ttitle = {A decade of progress on anisotropic mesh adaptation for computational fluid dynamics},\n\tvolume = {72},\n\tissn = {0010-4485},\n\tdoi = {10.1016/j.cad.2015.09.005},\n\tabstract = {In the context of scientific computing, the mesh is used as a discrete support for the considered numerical methods. As a consequence, the mesh greatly impacts the efficiency, the stability and the accuracy of numerical methods. The goal of anisotropic mesh adaptation is to generate a mesh which fits the application and the numerical scheme in order to achieve the best possible solution. It is thus an active field of research which is progressing continuously. This review article proposes a synthesis of the research activity of the INRIA Gamma3 team in the field of anisotropic mesh adaptation applied to inviscid flows in computational fluid dynamics since 2000. It shows the evolution of the theoretical and numerical results during this period. Finally, challenges for the next decade are discussed.},\n\tjournal = {23rd International Meshing Roundtable Special Issue: Advances in Mesh Generation},\n\tauthor = {Alauzet, Frédéric and Loseille, Adrien},\n\tmonth = mar,\n\tyear = {2016},\n\tkeywords = {Anisotropic mesh adaptation, Computational fluid dynamic, Continuous mesh framework, Inviscid flows, Metric},\n\tpages = {13--39},\n}\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n
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\n In the context of scientific computing, the mesh is used as a discrete support for the considered numerical methods. As a consequence, the mesh greatly impacts the efficiency, the stability and the accuracy of numerical methods. The goal of anisotropic mesh adaptation is to generate a mesh which fits the application and the numerical scheme in order to achieve the best possible solution. It is thus an active field of research which is progressing continuously. This review article proposes a synthesis of the research activity of the INRIA Gamma3 team in the field of anisotropic mesh adaptation applied to inviscid flows in computational fluid dynamics since 2000. It shows the evolution of the theoretical and numerical results during this period. Finally, challenges for the next decade are discussed.\n
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\n  \n 2015\n \n \n (30)\n \n \n
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\n \n\n \n \n Bradford, A.; Markusic, T.; and Sabripour, S.\n\n\n \n \n \n \n Firefly - New Generation of Low Cost, Small Launch Vehicles Designed to Serve the Rapidly Growing Small Satellite Market.\n \n \n \n\n\n \n\n\n\n In Oxford, UK, November 2015. Springer\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@inproceedings{bradford2015,\n\taddress = {Oxford, UK},\n\ttitle = {Firefly - {New} {Generation} of {Low} {Cost}, {Small} {Launch} {Vehicles} {Designed} to {Serve} the {Rapidly} {Growing} {Small} {Satellite} {Market}},\n\tdoi = {https://doi.org/10.1007/978-3-319-32817-1_5},\n\tpublisher = {Springer},\n\tauthor = {Bradford, Andy and Markusic, Tom and Sabripour, Shey},\n\tmonth = nov,\n\tyear = {2015},\n}\n\n\n\n
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\n \n\n \n \n Hatton, S.\n\n\n \n \n \n \n Proceedings of the 13th Reinventing Space Conference.\n \n \n \n\n\n \n\n\n\n Springer, November 2015.\n \n\n\n\n
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@book{hatton2015,\n\ttitle = {Proceedings of the 13th {Reinventing} {Space} {Conference}},\n\tisbn = {978-3-319-32816-4},\n\tpublisher = {Springer},\n\tauthor = {Hatton, Scott},\n\tmonth = nov,\n\tyear = {2015},\n}\n\n\n\n
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\n \n\n \n \n Scheiner, B.; Baalrud, S. D.; Yee, B. T.; Hopkins, M. M.; and Barnat, E. V.\n\n\n \n \n \n \n Theory of the electron sheath and presheath.\n \n \n \n\n\n \n\n\n\n Physics of Plasmas, 22(12): 123520. December 2015.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@article{scheiner2015,\n\ttitle = {Theory of the electron sheath and presheath},\n\tvolume = {22},\n\tissn = {1070-664X},\n\tdoi = {10.1063/1.4939024},\n\tabstract = {Electron sheaths are commonly found near Langmuir probes collecting the electron saturation current. The common assumption is that the probe collects the random flux of electrons incident on the sheath, which tacitly implies that there is no electron presheath and that the flux collected is due to a velocity space truncation of the electron velocity distribution function (EVDF). This work provides a dedicated theory of electron sheaths, which suggests that they are not so simple. Motivated by EVDFs observed in particle-in-cell (PIC) simulations, a 1D model for the electron sheath and presheath is developed. In the model, under low temperature plasma conditions (Te≫Ti), an electron pressure gradient accelerates electrons in the presheath to a flow velocity that exceeds the electron thermal speed at the sheath edge. This pressure gradient generates large flow velocities compared to what would be generated by ballistic motion in response to the electric field. It is found that in many situations, under common plasma conditions, the electron presheath extends much further into the plasma than an analogous ion presheath. PIC simulations reveal that the ion density in the electron presheath is determined by a flow around the electron sheath and that this flow is due to 2D aspects of the sheath geometry. Simulations also indicate the presence of ion acoustic instabilities excited by the differential flow between electrons and ions in the presheath, which result in sheath edge fluctuations. The 1D model and time averaged PIC simulations are compared and it is shown that the model provides a good description of the electron sheath and presheath.},\n\tnumber = {12},\n\turldate = {2024-04-24},\n\tjournal = {Physics of Plasmas},\n\tauthor = {Scheiner, Brett and Baalrud, Scott D. and Yee, Benjamin T. and Hopkins, Matthew M. and Barnat, Edward V.},\n\tmonth = dec,\n\tyear = {2015},\n\tpages = {123520},\n}\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n
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\n Electron sheaths are commonly found near Langmuir probes collecting the electron saturation current. The common assumption is that the probe collects the random flux of electrons incident on the sheath, which tacitly implies that there is no electron presheath and that the flux collected is due to a velocity space truncation of the electron velocity distribution function (EVDF). This work provides a dedicated theory of electron sheaths, which suggests that they are not so simple. Motivated by EVDFs observed in particle-in-cell (PIC) simulations, a 1D model for the electron sheath and presheath is developed. In the model, under low temperature plasma conditions (Te≫Ti), an electron pressure gradient accelerates electrons in the presheath to a flow velocity that exceeds the electron thermal speed at the sheath edge. This pressure gradient generates large flow velocities compared to what would be generated by ballistic motion in response to the electric field. It is found that in many situations, under common plasma conditions, the electron presheath extends much further into the plasma than an analogous ion presheath. PIC simulations reveal that the ion density in the electron presheath is determined by a flow around the electron sheath and that this flow is due to 2D aspects of the sheath geometry. Simulations also indicate the presence of ion acoustic instabilities excited by the differential flow between electrons and ions in the presheath, which result in sheath edge fluctuations. The 1D model and time averaged PIC simulations are compared and it is shown that the model provides a good description of the electron sheath and presheath.\n
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\n \n\n \n \n Ali, A. R. A.; and Janajreh, I.\n\n\n \n \n \n \n \n Numerical Simulation of Turbine Blade Cooling via Jet Impingement.\n \n \n \n \n\n\n \n\n\n\n Energy Procedia, 75: 3220–3229. August 2015.\n \n\n\n\n
\n\n\n\n \n \n \"NumericalPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n\n\n\n
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@article{ali2015,\n\tseries = {Clean, {Efficient} and {Affordable} {Energy} for a {Sustainable} {Future}: {The} 7th {International} {Conference} on {Applied} {Energy} ({ICAE2015})},\n\ttitle = {Numerical {Simulation} of {Turbine} {Blade} {Cooling} via {Jet} {Impingement}},\n\tvolume = {75},\n\tissn = {1876-6102},\n\turl = {https://www.sciencedirect.com/science/article/pii/S1876610215014514},\n\tdoi = {10.1016/j.egypro.2015.07.683},\n\tabstract = {Various industrial applications use jet impingement against surface to provide an effective mode of heat transfer. Its application includes, but not limited to, heat treatment, thermal management of optical surfaces for defogging, cooling of critical machinery structures, and rocket launcher cooling. In this study, numerical analysis of various heat transfer configurations of jet impingement on a semi-circular surface is carried out. These configurations were compared on the basis of effective heat transfer by achieving higher Nusselt number and lower surface temperature as convection heat is becoming the dominant phenomenon. The numerical model was developed for considering the application of a uniform heat flux on a curved surface subjected to jet flow that simulating an internal channel under cooling. The results found to be in agreement with the literature experimental data. To gain more insight on the underlining physics of the flow, a sensitivity analysis on the jet impingement configuration and flow conditions were conducted and was demonstrated to the inner cooling of the 1st stage gas turbine blade.},\n\turldate = {2024-04-24},\n\tjournal = {Energy Procedia},\n\tauthor = {Ali, Abdulla R. Al and Janajreh, Isam},\n\tmonth = aug,\n\tyear = {2015},\n\tkeywords = {Nusselt number, jetcooling, serpantine, turbine blade cooling},\n\tpages = {3220--3229},\n}\n\n\n\n\n\n\n\n
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\n Various industrial applications use jet impingement against surface to provide an effective mode of heat transfer. Its application includes, but not limited to, heat treatment, thermal management of optical surfaces for defogging, cooling of critical machinery structures, and rocket launcher cooling. In this study, numerical analysis of various heat transfer configurations of jet impingement on a semi-circular surface is carried out. These configurations were compared on the basis of effective heat transfer by achieving higher Nusselt number and lower surface temperature as convection heat is becoming the dominant phenomenon. The numerical model was developed for considering the application of a uniform heat flux on a curved surface subjected to jet flow that simulating an internal channel under cooling. The results found to be in agreement with the literature experimental data. To gain more insight on the underlining physics of the flow, a sensitivity analysis on the jet impingement configuration and flow conditions were conducted and was demonstrated to the inner cooling of the 1st stage gas turbine blade.\n
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\n \n\n \n \n Zhu, S. X.; Michael, H. C.; and Mrityunjay, S.\n\n\n \n \n \n \n Additive Manufacturing of Silicon Carbide-Based Ceramics By 3-D Printing Technologies.\n \n \n \n\n\n \n\n\n\n In Advanced Processing and Manufacturing Technologies for Nanostructured and Multifunctional Materials II, pages 133–144. John Wiley & Sons, Ltd, 2015.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@incollection{zhu_additive_2015,\n\ttitle = {Additive {Manufacturing} of {Silicon} {Carbide}-{Based} {Ceramics} {By} 3-{D} {Printing} {Technologies}},\n\tcopyright = {Copyright © 2016 by The American Ceramic Society. All rights reserved.},\n\tisbn = {978-1-119-21166-2},\n\tabstract = {Silicon carbide (SiC)-based materials are needed for a number of high temperature applications due to their excellent strength, thermal stability, and oxidation resistance. Fabrication of functional SiC ceramics by additive manufacturing technologies greatly reduces production time and cost, particularly for small production quantities necessary for prototype development. Two approaches which utilize 3-D printing technologies to obtain a SiC ceramic were investigated in this study. Various shapes with engineered porosity were printed using a commercially available wood filament which served as a carbonaceous preform. The printed samples were infiltrated with a pre-ceramic polymer containing dip-coat solution then pyrolyzed. The effect of solution composition on structure retention and conversion to SiC were investigated. In the second approach, pre-ceramic pastes comprised of SiC, silicon (Si), and carbon (C) particulates were evaluated as a potential extruder feedstock. Characteristic decomposition patterns in nitrogen and air were observed using thermogravimetric analysis (TGA), and X-Ray Diffraction (XRD) was used for phase identification. The effect of Si addition, SiC particle size, and pyrolysis conditions on the conversion to SiC has been studied.},\n\tlanguage = {en},\n\turldate = {2023-10-28},\n\tbooktitle = {Advanced {Processing} and {Manufacturing} {Technologies} for {Nanostructured} and {Multifunctional} {Materials} {II}},\n\tpublisher = {John Wiley \\& Sons, Ltd},\n\tauthor = {Zhu, Shirley X. and Michael, Halbig C. and Mrityunjay, Singh},\n\tyear = {2015},\n\tkeywords = {3-d printing technology, carbide-based ceramic, extruder feedstock, phase identification},\n\tpages = {133--144},\n}\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n
\n
\n\n\n
\n Silicon carbide (SiC)-based materials are needed for a number of high temperature applications due to their excellent strength, thermal stability, and oxidation resistance. Fabrication of functional SiC ceramics by additive manufacturing technologies greatly reduces production time and cost, particularly for small production quantities necessary for prototype development. Two approaches which utilize 3-D printing technologies to obtain a SiC ceramic were investigated in this study. Various shapes with engineered porosity were printed using a commercially available wood filament which served as a carbonaceous preform. The printed samples were infiltrated with a pre-ceramic polymer containing dip-coat solution then pyrolyzed. The effect of solution composition on structure retention and conversion to SiC were investigated. In the second approach, pre-ceramic pastes comprised of SiC, silicon (Si), and carbon (C) particulates were evaluated as a potential extruder feedstock. Characteristic decomposition patterns in nitrogen and air were observed using thermogravimetric analysis (TGA), and X-Ray Diffraction (XRD) was used for phase identification. The effect of Si addition, SiC particle size, and pyrolysis conditions on the conversion to SiC has been studied.\n
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\n \n\n \n \n Bitter, N. P.; and Shepherd, J. E.\n\n\n \n \n \n \n Stability of highly cooled hypervelocity boundary layers.\n \n \n \n\n\n \n\n\n\n Journal of Fluid Mechanics, 778: 586–620. September 2015.\n Publisher: Cambridge University Press\n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{bitter2015,\n\ttitle = {Stability of highly cooled hypervelocity boundary layers},\n\tvolume = {778},\n\tissn = {0022-1120, 1469-7645},\n\tdoi = {10.1017/jfm.2015.358},\n\tabstract = {The influence of high levels of wall cooling on the stability of hypervelocity boundary layers is investigated. Such conditions are relevant to experiments in high-enthalpy impulse facilities, where the wall temperature is much smaller than the free-stream temperature, as well as to some real flight scenarios. Some effects of wall cooling are well known, for instance, the stabilization of the first mode and destabilization of the second mode. In this paper, several new instability phenomena are investigated that arise only for high Mach numbers and high levels of wall cooling. In particular, certain unstable modes can travel supersonically with respect to the free stream, which changes the nature of the dispersion curve and leads to instability over a much wider band of frequencies. The cause of this phenomenon, the range of parameters for which it occurs and its implications for boundary layer stability are examined. Additionally, growth rates are systematically reported for a wide range of conditions relevant to high-enthalpy impulse facilities, and the stability trends in terms of Mach number and wall temperature are mapped out. Thermal non-equilibrium is included in the analysis and its influence on the stability characteristics of flows in impulse facilities is assessed.},\n\tlanguage = {en},\n\turldate = {2023-08-08},\n\tjournal = {Journal of Fluid Mechanics},\n\tauthor = {Bitter, N. P. and Shepherd, J. E.},\n\tmonth = sep,\n\tyear = {2015},\n\tnote = {Publisher: Cambridge University Press},\n\tkeywords = {boundary layer stability, compressible flows, transition to turbulence},\n\tpages = {586--620},\n}\n\n\n\n\n\n\n\n
\n
\n\n\n
\n The influence of high levels of wall cooling on the stability of hypervelocity boundary layers is investigated. Such conditions are relevant to experiments in high-enthalpy impulse facilities, where the wall temperature is much smaller than the free-stream temperature, as well as to some real flight scenarios. Some effects of wall cooling are well known, for instance, the stabilization of the first mode and destabilization of the second mode. In this paper, several new instability phenomena are investigated that arise only for high Mach numbers and high levels of wall cooling. In particular, certain unstable modes can travel supersonically with respect to the free stream, which changes the nature of the dispersion curve and leads to instability over a much wider band of frequencies. The cause of this phenomenon, the range of parameters for which it occurs and its implications for boundary layer stability are examined. Additionally, growth rates are systematically reported for a wide range of conditions relevant to high-enthalpy impulse facilities, and the stability trends in terms of Mach number and wall temperature are mapped out. Thermal non-equilibrium is included in the analysis and its influence on the stability characteristics of flows in impulse facilities is assessed.\n
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\n \n\n \n \n Sanchez, R.; Palacios, R.; Economon, T. D.; Kline, H. L.; Alonso, J. J.; and Palacios, F.\n\n\n \n \n \n \n Towards a fluid-structure interaction solver for problems with large deformations within the open-source SU2 suite.\n \n \n \n\n\n \n\n\n\n In 2015. AIAA Paper 2016-0205\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{sanchez2015,\n\ttitle = {Towards a fluid-structure interaction solver for problems with large deformations within the open-source {SU2} suite},\n\tisbn = {978-1-62410-392-6},\n\tdoi = {10.2514/6.2016-0205},\n\tabstract = {This paper describes a new framework for Fluid-Structure Interaction (FSI) modelling within the open-source code SU2. SU2 has been developed to solve complex, multi-physics problems described by Partial Differential Equations (PDEs), with an emphasis on problems involving aerodynamic shape optimization. Due to its modularity, the code provides an appropriate infrastructure for the solution of physical problems in several disciplines. This work provides SU2 with new tools that expand its capabilities in the fields of structural analysis and FSI. The focus will be on geometrically-nonlinear deformable solids in low-speed external ows. A Finite Element (FE) structural solver, able to deal with geometrical and material non-linearities in a static and a dynamic setting, has been built within the framework of SU2 alongside the existing solvers. Following the original object-oriented architecture in C++, a new structure compliant with the CFD solver has been developed. These new features will serve as a basis for future developments of FE-based strategies for the solution of PDEs. The structural solver has been coupled with the original uid solver in SU2 using a partitioned approach. The structure of the code was fully recast to allow analysis across multiple zones and physical problems, currently limited to problems involving uid and structural analysis. Both loosely-and strongly-coupled strategies are available for the solution of the coupled FSI problem. Finally, the validity of the implementations is assessed by studying the behavior of a rigid square with a exible cantilever at low Reynolds number. The results obtained demonstrate the capabilities of these new developments and further address the physics behind this benchmark problem.},\n\tpublisher = {AIAA Paper 2016-0205},\n\tauthor = {Sanchez, Ruben and Palacios, Rafael and Economon, Thomas D. and Kline, Heather L. and Alonso, Juan J. and Palacios, Francisco},\n\tyear = {2015},\n}\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n
\n
\n\n\n
\n This paper describes a new framework for Fluid-Structure Interaction (FSI) modelling within the open-source code SU2. SU2 has been developed to solve complex, multi-physics problems described by Partial Differential Equations (PDEs), with an emphasis on problems involving aerodynamic shape optimization. Due to its modularity, the code provides an appropriate infrastructure for the solution of physical problems in several disciplines. This work provides SU2 with new tools that expand its capabilities in the fields of structural analysis and FSI. The focus will be on geometrically-nonlinear deformable solids in low-speed external ows. A Finite Element (FE) structural solver, able to deal with geometrical and material non-linearities in a static and a dynamic setting, has been built within the framework of SU2 alongside the existing solvers. Following the original object-oriented architecture in C++, a new structure compliant with the CFD solver has been developed. These new features will serve as a basis for future developments of FE-based strategies for the solution of PDEs. The structural solver has been coupled with the original uid solver in SU2 using a partitioned approach. The structure of the code was fully recast to allow analysis across multiple zones and physical problems, currently limited to problems involving uid and structural analysis. Both loosely-and strongly-coupled strategies are available for the solution of the coupled FSI problem. Finally, the validity of the implementations is assessed by studying the behavior of a rigid square with a exible cantilever at low Reynolds number. The results obtained demonstrate the capabilities of these new developments and further address the physics behind this benchmark problem.\n
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\n \n\n \n \n Berger, K. T.; Hollingsworth, K. E.; Wright, S. A.; and Rufer, S. J.\n\n\n \n \n \n \n NASA Langley Aerothermodynamics Laboratory: Hypersonic Testing Capabilities.\n \n \n \n\n\n \n\n\n\n In 53rd AIAA Aerospace Sciences Meeting, Kissimmee, Florida, January 2015. AIAA Paper 2015-1337\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{berger2015,\n\taddress = {Kissimmee, Florida},\n\ttitle = {{NASA} {Langley} {Aerothermodynamics} {Laboratory}: {Hypersonic} {Testing} {Capabilities}},\n\tisbn = {978-1-62410-343-8},\n\tshorttitle = {{NASA} {Langley} {Aerothermodynamics} {Laboratory}},\n\tdoi = {10.2514/6.2015-1337},\n\tlanguage = {en},\n\turldate = {2023-08-03},\n\tbooktitle = {53rd {AIAA} {Aerospace} {Sciences} {Meeting}},\n\tpublisher = {AIAA Paper 2015-1337},\n\tauthor = {Berger, Karen T. and Hollingsworth, Kevin E. and Wright, Shelia A. and Rufer, Shann J.},\n\tmonth = jan,\n\tyear = {2015},\n}\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n
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\n \n\n \n \n Chen, C.; Lv, S.; Li, J.; Wang, Z.; Liang, X.; Li, Y.; Viehland, D.; Nakajima, K.; and Ikuhara, Y.\n\n\n \n \n \n \n Two-dimensional electron gas at the Ti-diffused BiFeO3/SrTiO3 interface.\n \n \n \n\n\n \n\n\n\n Applied Physics Letters, 107(3): 031601–031601. July 2015.\n Publisher: AIP Publishing LLCAIP Publishing\n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{chen2015,\n\ttitle = {Two-dimensional electron gas at the {Ti}-diffused {BiFeO3}/{SrTiO3} interface},\n\tvolume = {107},\n\tdoi = {10.1063/1.4926732},\n\tabstract = {Oxide heterostructures with the broken translational symmetry often trigger a two-dimensional quantum confinement and associated unique electronic properties that cannot be observed in bulk constit...},\n\tnumber = {3},\n\tjournal = {Applied Physics Letters},\n\tauthor = {Chen, Chunlin and Lv, Shuhui and Li, Junjie and Wang, Zhongchang and Liang, Xiaobin and Li, Yanxi and Viehland, Dwight and Nakajima, Ken and Ikuhara, Yuichi},\n\tmonth = jul,\n\tyear = {2015},\n\tnote = {Publisher: AIP Publishing LLCAIP Publishing},\n\tkeywords = {ab initio calculations, atomic force microscopy, bismuth compounds, chemical interdiffusion, strontium compounds, transmission electron microscopy, two-dimensional electron gas, valence bands},\n\tpages = {031601--031601},\n}\n\n\n\n
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\n Oxide heterostructures with the broken translational symmetry often trigger a two-dimensional quantum confinement and associated unique electronic properties that cannot be observed in bulk constit...\n
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\n \n\n \n \n Burnaev, E. V.; and Zaytsev, A. A.\n\n\n \n \n \n \n \n Surrogate modeling of multifidelity data for large samples.\n \n \n \n \n\n\n \n\n\n\n Journal of Communications Technology and Electronics 2015 60:12, 60(12): 1348–1355. December 2015.\n Publisher: Springer\n\n\n\n
\n\n\n\n \n \n \"SurrogatePaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n\n\n\n
\n 
@article{burnaev2015,\n\ttitle = {Surrogate modeling of multifidelity data for large samples},\n\tvolume = {60},\n\turl = {https://link.springer.com/article/10.1134/S1064226915120037},\n\tdoi = {10.1134/S1064226915120037},\n\tabstract = {The problem of construction of a surrogate model based on available lowand high-fidelity data is considered. The low-fidelity data can be obtained, e.g., by performing the computer simulation and the high-fidelity data can be obtained by performing experiments in a wind tunnel. A regression model based on Gaussian processes proves to be convenient for modeling variable-fidelity data. Using this model, one can efficiently reconstruct nonlinear dependences and estimate the prediction accuracy at a specified point. However, if the sample size exceeds several thousand points, direct use of the Gaussian process regression becomes impossible due to a high computational complexity of the algorithm. We develop new algorithms for processing multifidelity data based on Gaussian process model, which are efficient even for large samples. We illustrate application of the developed algorithms by constructing surrogate models of a complex engineering system.},\n\tnumber = {12},\n\tjournal = {Journal of Communications Technology and Electronics 2015 60:12},\n\tauthor = {Burnaev, E. V. and Zaytsev, A. A.},\n\tmonth = dec,\n\tyear = {2015},\n\tnote = {Publisher: Springer},\n\tkeywords = {Communications Engineering, Networks},\n\tpages = {1348--1355},\n}\n\n\n\n
\n
\n\n\n
\n The problem of construction of a surrogate model based on available lowand high-fidelity data is considered. The low-fidelity data can be obtained, e.g., by performing the computer simulation and the high-fidelity data can be obtained by performing experiments in a wind tunnel. A regression model based on Gaussian processes proves to be convenient for modeling variable-fidelity data. Using this model, one can efficiently reconstruct nonlinear dependences and estimate the prediction accuracy at a specified point. However, if the sample size exceeds several thousand points, direct use of the Gaussian process regression becomes impossible due to a high computational complexity of the algorithm. We develop new algorithms for processing multifidelity data based on Gaussian process model, which are efficient even for large samples. We illustrate application of the developed algorithms by constructing surrogate models of a complex engineering system.\n
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\n \n\n \n \n Martin, A.; and Boyd, I. D.\n\n\n \n \n \n \n \n Strongly Coupled Computation of Material Response and Nonequilibrium Flow for Hypersonic Ablation.\n \n \n \n \n\n\n \n\n\n\n Journal of Spacecraft and Rockets, 52(1): 89–104. February 2015.\n Publisher: American Institute of Aeronautics and Astronautics\n\n\n\n
\n\n\n\n \n \n \"StronglyPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{martin2015,\n\ttitle = {Strongly {Coupled} {Computation} of {Material} {Response} and {Nonequilibrium} {Flow} for {Hypersonic} {Ablation}},\n\tvolume = {52},\n\turl = {https://arc.aiaa.org/doi/abs/10.2514/1.A32847},\n\tdoi = {10.2514/1.A32847},\n\tabstract = {The steps necessary to achieve the strong coupling between a flowfield solver and a material response solver are presented. This type of coupling is required to accurately capture the complex aerot...},\n\tnumber = {1},\n\tjournal = {Journal of Spacecraft and Rockets},\n\tauthor = {Martin, Alexandre and Boyd, Iain D.},\n\tmonth = feb,\n\tyear = {2015},\n\tnote = {Publisher: American Institute of Aeronautics and Astronautics},\n\tkeywords = {Arbitrary Lagrangian Eulerian, Boundary Layer, Courant Friedrichs Lewy, Freestream Mach Number, Heat Flux, Hypersonic Ablation, Hypersonic Aerothermodynamics, Nonequilibrium Flows, Pyrolysis, Stagnation Point},\n\tpages = {89--104},\n}\n\n\n\n
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\n The steps necessary to achieve the strong coupling between a flowfield solver and a material response solver are presented. This type of coupling is required to accurately capture the complex aerot...\n
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\n \n\n \n \n Luquet, D.; Marchiano, R.; Coulouvrat, F.; Salah El Din, I.; and Loseille, A.\n\n\n \n \n \n \n Sonic Boom Assessment of a Hypersonic Transport Vehicle with Advanced Numerical Methods.\n \n \n \n\n\n \n\n\n\n In pages 1–13, 2015. \\AIAA Paper\\ 2015-2685\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{luquet2015,\n\ttitle = {Sonic {Boom} {Assessment} of a {Hypersonic} {Transport} {Vehicle} with {Advanced} {Numerical} {Methods}},\n\tdoi = {10.2514/6.2015-2685},\n\tpublisher = {\\{AIAA Paper\\} 2015-2685},\n\tauthor = {Luquet, David and Marchiano, Régis and Coulouvrat, François and Salah El Din, Itham and Loseille, Adrien},\n\tyear = {2015},\n\tpages = {1--13},\n}\n\n\n\n
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\n \n\n \n \n Gaitonde, D. V.\n\n\n \n \n \n \n \n Progress in shock wave/boundary layer interactions.\n \n \n \n \n\n\n \n\n\n\n Celebrating 60 Years of the Air Force Office of Scientific Research (AFOSR): A Review of Hypersonic Aerothermodynamics, 72: 80–99. January 2015.\n \n\n\n\n
\n\n\n\n \n \n \"ProgressPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{gaitonde2015,\n\ttitle = {Progress in shock wave/boundary layer interactions},\n\tvolume = {72},\n\tissn = {0376-0421},\n\turl = {https://www.sciencedirect.com/science/article/pii/S0376042114000815},\n\tdoi = {10.1016/j.paerosci.2014.09.002},\n\tabstract = {Recent advances in shock wave boundary layer interaction research are reviewed in four areas: (i) understanding low frequency unsteadiness, (ii) heat transfer prediction capability, (iii) phenomena in complex (multi-shock boundary layer) interactions and (iv) flow control techniques. Substantial success has been achieved in describing the phenomenology of low frequency unsteadiness, including correlations and coherent structures in the separation bubble, through complementary experimental and numerical studies on nominally 2-D interactions. These observations have been parlayed to propose underlying mechanisms based on oscillation, amplification and upstream boundary layer effects. For heat transfer prediction capability, systematic studies conducted under the auspices of AFOSR and RTO-AVT activities have shown that for axisymmetric laminar situations, heat transfer rates can be measured, and in many cases predicted, reasonably accurately even in the presence of high-temperature effects. Efforts have quantified uncertainty of Reynolds averaged turbulence models, and hybrid methods have been developed to at least partially address deficiencies. Progress in complex interactions encompass two of the major phenomena affected by SBLI in scramjet flowpaths: unstart and mode transition from ramjet (dual mode) to scramjet. Control studies have attempted to leverage the better understanding of the fundamental phenomena with passive and active techniques, the latter exploiting the superior properties of newer actuators. Objectives include reduction in size of the separation region, surface loads and modulation of spectral content. Finally, SBLI studies have benefited handsomely from successful ground and flight test campaigns associated with the HIFiRE-1 and HIFiRE-2 campaigns, results from which are woven into the discussion, as are limitations in current capability and understanding.},\n\tjournal = {Celebrating 60 Years of the Air Force Office of Scientific Research (AFOSR): A Review of Hypersonic Aerothermodynamics},\n\tauthor = {Gaitonde, Datta V.},\n\tmonth = jan,\n\tyear = {2015},\n\tkeywords = {Separated flows, Shock boundary layer interactions, Viscous–inviscid interactions},\n\tpages = {80--99},\n}\n\n\n\n
\n
\n\n\n
\n Recent advances in shock wave boundary layer interaction research are reviewed in four areas: (i) understanding low frequency unsteadiness, (ii) heat transfer prediction capability, (iii) phenomena in complex (multi-shock boundary layer) interactions and (iv) flow control techniques. Substantial success has been achieved in describing the phenomenology of low frequency unsteadiness, including correlations and coherent structures in the separation bubble, through complementary experimental and numerical studies on nominally 2-D interactions. These observations have been parlayed to propose underlying mechanisms based on oscillation, amplification and upstream boundary layer effects. For heat transfer prediction capability, systematic studies conducted under the auspices of AFOSR and RTO-AVT activities have shown that for axisymmetric laminar situations, heat transfer rates can be measured, and in many cases predicted, reasonably accurately even in the presence of high-temperature effects. Efforts have quantified uncertainty of Reynolds averaged turbulence models, and hybrid methods have been developed to at least partially address deficiencies. Progress in complex interactions encompass two of the major phenomena affected by SBLI in scramjet flowpaths: unstart and mode transition from ramjet (dual mode) to scramjet. Control studies have attempted to leverage the better understanding of the fundamental phenomena with passive and active techniques, the latter exploiting the superior properties of newer actuators. Objectives include reduction in size of the separation region, surface loads and modulation of spectral content. Finally, SBLI studies have benefited handsomely from successful ground and flight test campaigns associated with the HIFiRE-1 and HIFiRE-2 campaigns, results from which are woven into the discussion, as are limitations in current capability and understanding.\n
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\n \n\n \n \n Liechty, D. S.\n\n\n \n \n \n \n \n Object-oriented/data-oriented design of a direct simulation Monte Carlo algorithm.\n \n \n \n \n\n\n \n\n\n\n Journal of Spacecraft and Rockets, 52(6): 1521–1529. October 2015.\n Publisher: American Institute of Aeronautics and Astronautics Inc.\n\n\n\n
\n\n\n\n \n \n \"Object-oriented/data-orientedPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{liechty2015,\n\ttitle = {Object-oriented/data-oriented design of a direct simulation {Monte} {Carlo} algorithm},\n\tvolume = {52},\n\turl = {https://arc.aiaa.org/doi/10.2514/1.A33177},\n\tdoi = {10.2514/1.A33177/ASSET/IMAGES/LARGE/FIGURE8.JPEG},\n\tabstract = {National Aeronautics and Space Administration has been investing in the development of a new code, the Multiphysics Algorithm with Particles, to incorporate recent developments in direct simulation Monte Carlo algorithms and improve physical realism, time to solution, and expand the range of usefulness of National Aeronautics and Space Administration direct simulation Monte Carlo codes (in both velocity space and altitude). The Multiphysics Algorithm with Particles is an object-oriented/data-oriented code written in C++. Object-oriented codes are likely the most flexible and efficient approach for the development of new algorithms and physics modules due to their inherent modularity. However, computational efficiency is an equally critical component of software design that must be considered, which is why data-oriented design becomes important. The focus of the development of the Multiphysics Algorithm with Particles thus far has been on the creation of efficient particle data structures, the inclusion of gas models, and the ability to dynamically adapt a simulation. Future work will focus on more efficient grid structures and parallel computing strategies. The new software is evaluated in the current study with regard to 1) software design and extensibility, 2) accuracy of solution, and 3) efficiency of solution. For each category, comparisons will be made against legacy software to identify the relative merits of each software package. For software design and extensibility, the details of the Software Engineering Plan for the Multiphysics Algorithm with Particles will be presented. For accuracy of solution, comparisons will be made to test cases from the literature. Speed comparisons are made between the Multiphysics Algorithm with Particles and the current production direct simulation Monte Carlo code at National Aeronautics and Space Administration, the direct simulation Monte Carlo Analysis Code, for both serial and parallel implementations. More importantly, though, are the automated grid, time step, and surface temperature adaptation algorithms included in the Multiphysics Algorithm with Particles. The user can now specify the simulation initial conditions and begin the solution one time, and the Multiphysics Algorithm with Particles automatically adapts the solution and determines when the final solution has been reached.},\n\tnumber = {6},\n\tjournal = {Journal of Spacecraft and Rockets},\n\tauthor = {Liechty, Derek S.},\n\tmonth = oct,\n\tyear = {2015},\n\tnote = {Publisher: American Institute of Aeronautics and Astronautics Inc.},\n\tkeywords = {C++ Programming Language, Data Structures, Direct Simulation Monte Carlo, Freestream, Knudsen Numbers, NASA Langley Research Center, National Aeronautics and Space Administration, Number of Particles, Parallel Computing Strategies, Software Design‎},\n\tpages = {1521--1529},\n}\n\n\n\n
\n
\n\n\n
\n National Aeronautics and Space Administration has been investing in the development of a new code, the Multiphysics Algorithm with Particles, to incorporate recent developments in direct simulation Monte Carlo algorithms and improve physical realism, time to solution, and expand the range of usefulness of National Aeronautics and Space Administration direct simulation Monte Carlo codes (in both velocity space and altitude). The Multiphysics Algorithm with Particles is an object-oriented/data-oriented code written in C++. Object-oriented codes are likely the most flexible and efficient approach for the development of new algorithms and physics modules due to their inherent modularity. However, computational efficiency is an equally critical component of software design that must be considered, which is why data-oriented design becomes important. The focus of the development of the Multiphysics Algorithm with Particles thus far has been on the creation of efficient particle data structures, the inclusion of gas models, and the ability to dynamically adapt a simulation. Future work will focus on more efficient grid structures and parallel computing strategies. The new software is evaluated in the current study with regard to 1) software design and extensibility, 2) accuracy of solution, and 3) efficiency of solution. For each category, comparisons will be made against legacy software to identify the relative merits of each software package. For software design and extensibility, the details of the Software Engineering Plan for the Multiphysics Algorithm with Particles will be presented. For accuracy of solution, comparisons will be made to test cases from the literature. Speed comparisons are made between the Multiphysics Algorithm with Particles and the current production direct simulation Monte Carlo code at National Aeronautics and Space Administration, the direct simulation Monte Carlo Analysis Code, for both serial and parallel implementations. More importantly, though, are the automated grid, time step, and surface temperature adaptation algorithms included in the Multiphysics Algorithm with Particles. The user can now specify the simulation initial conditions and begin the solution one time, and the Multiphysics Algorithm with Particles automatically adapts the solution and determines when the final solution has been reached.\n
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\n \n\n \n \n Henneton, M.; Gainville, O.; and Coulouvrat, F.\n\n\n \n \n \n \n \n Numerical Simulation of Sonic Boom from Hypersonic Meteoroids.\n \n \n \n \n\n\n \n\n\n\n AIAA Journal, 53(9): 2560–2570. September 2015.\n Publisher: American Institute of Aeronautics and Astronautics Inc.\n\n\n\n
\n\n\n\n \n \n \"NumericalPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{henneton2015,\n\ttitle = {Numerical {Simulation} of {Sonic} {Boom} from {Hypersonic} {Meteoroids}},\n\tvolume = {53},\n\turl = {http://arc.aiaa.org/doi/10.2514/1.J053421},\n\tdoi = {10.2514/1.J053421},\n\tabstract = {Meteoroids entering the Earth atmosphere at high hypersonic velocities are sources of sonic booms that are recorded as infrasound signals at the ground level. The boom pressure field is simulated by solving Euler equations for a spherical meteoroid. The numerical challenge is to capture the acoustical regime of weak shock waves in the very far field at several hundreds or thousands times the meteoroid diameter. Computational fluid dynamics simulations are then matched to nonlinear geometrical acoustics for long-range atmospheric propagation down to the ground. The numerical process is validated through comparison with an analytical model, considering for perfect gases the meteoroid as a line source of strong shock in the near field, matched to a weak shock N-wave in the far field. Compared with a perfect gas, real gas effects at thermochemical equilibrium induce a reduced amplitude at the source, along with a shorter signal duration at the ground level. Simulations are illustrated for the well-documented Carancas meteorite that impacted on Peru in 2007.},\n\tnumber = {9},\n\tjournal = {AIAA Journal},\n\tauthor = {Henneton, Martin and Gainville, Olaf and Coulouvrat, François},\n\tmonth = sep,\n\tyear = {2015},\n\tnote = {Publisher: American Institute of Aeronautics and Astronautics Inc.},\n\tpages = {2560--2570},\n}\n\n\n\n
\n
\n\n\n
\n Meteoroids entering the Earth atmosphere at high hypersonic velocities are sources of sonic booms that are recorded as infrasound signals at the ground level. The boom pressure field is simulated by solving Euler equations for a spherical meteoroid. The numerical challenge is to capture the acoustical regime of weak shock waves in the very far field at several hundreds or thousands times the meteoroid diameter. Computational fluid dynamics simulations are then matched to nonlinear geometrical acoustics for long-range atmospheric propagation down to the ground. The numerical process is validated through comparison with an analytical model, considering for perfect gases the meteoroid as a line source of strong shock in the near field, matched to a weak shock N-wave in the far field. Compared with a perfect gas, real gas effects at thermochemical equilibrium induce a reduced amplitude at the source, along with a shorter signal duration at the ground level. Simulations are illustrated for the well-documented Carancas meteorite that impacted on Peru in 2007.\n
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\n \n\n \n \n Neitzel, K. J; Kim, J. G.; and Boyd, I. D\n\n\n \n \n \n \n Nonequilibrium Modeling of Oxygen in Reflected Shock Tube Flows.\n \n \n \n\n\n \n\n\n\n In Atlanta, GA, June 2015. \\AIAA Paper\\ 2014-2961\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{neitzel2015,\n\taddress = {Atlanta, GA},\n\ttitle = {Nonequilibrium {Modeling} of {Oxygen} in {Reflected} {Shock} {Tube} {Flows}},\n\tpublisher = {\\{AIAA Paper\\} 2014-2961},\n\tauthor = {Neitzel, Kevin J and Kim, Jae Gang and Boyd, Iain D},\n\tmonth = jun,\n\tyear = {2015},\n}\n\n\n\n
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\n \n\n \n \n Kundrapu, M.; Loverich, J.; Beckwith, K.; Stoltz, P.; Shashurin, A.; and Keidar, M.\n\n\n \n \n \n \n Modeling Radio Communication Blackout and Blackout Mitigation in Hypersonic Vehicles.\n \n \n \n\n\n \n\n\n\n Journal of Spacecraft and Rockets, 52(3): 853–862. May 2015.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{kundrapu2015,\n\ttitle = {Modeling {Radio} {Communication} {Blackout} and {Blackout} {Mitigation} in {Hypersonic} {Vehicles}},\n\tvolume = {52},\n\tnumber = {3},\n\tjournal = {Journal of Spacecraft and Rockets},\n\tauthor = {Kundrapu, Madhusudhan and Loverich, John and Beckwith, Kristian and Stoltz, Peter and Shashurin, Alexey and Keidar, Michael},\n\tmonth = may,\n\tyear = {2015},\n\tpages = {853--862},\n}\n\n\n\n
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\n \n\n \n \n Kim, J. G.; and Boyd, I. D.\n\n\n \n \n \n \n \n Master Equation Analysis of Post Normal Shock Waves of Nitrogen.\n \n \n \n \n\n\n \n\n\n\n Journal of Thermophysics and Heat Transfer, 29(2): 241–252. February 2015.\n Publisher: American Institute of Aeronautics and Astronautics\n\n\n\n
\n\n\n\n \n \n \"MasterPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{kim2015,\n\ttitle = {Master {Equation} {Analysis} of {Post} {Normal} {Shock} {Waves} of {Nitrogen}},\n\tvolume = {29},\n\turl = {https://arc.aiaa.org/doi/abs/10.2514/1.T4249},\n\tdoi = {10.2514/1.T4249},\n\tabstract = {One-dimensional post normal shock flow calculations are carried out using state-of-the-art thermochemical nonequilibrium models. Two-temperature, four-temperature, and electronic master equation co...},\n\tnumber = {2},\n\tjournal = {Journal of Thermophysics and Heat Transfer},\n\tauthor = {Kim, Jae Gang and Boyd, Iain D.},\n\tmonth = feb,\n\tyear = {2015},\n\tnote = {Publisher: American Institute of Aeronautics and Astronautics},\n\tkeywords = {Electron Temperature, Energy Conservation Equation, Freestream Conditions, Hypersonic Speed, NASA Ames Research Center, Normal Shock Wave, Rankine Hugoniot Relation, Spectrum Radiation, Spontaneous Emission, Vibrational Energy},\n\tpages = {241--252},\n}\n\n\n\n
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\n One-dimensional post normal shock flow calculations are carried out using state-of-the-art thermochemical nonequilibrium models. Two-temperature, four-temperature, and electronic master equation co...\n
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\n \n\n \n \n Josyula, E.,\n editor.\n \n\n\n \n \n \n \n Hypersonic Nonequilibrium Flows: Fundamentals and Recent Advances.\n \n \n \n\n\n \n\n\n\n AIAA, 2015.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@book{josyula2015a,\n\ttitle = {Hypersonic {Nonequilibrium} {Flows}: {Fundamentals} and {Recent} {Advances}},\n\tpublisher = {AIAA},\n\teditor = {Josyula, Eswar},\n\tyear = {2015},\n}\n\n\n\n
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\n \n\n \n \n Josyula, E.,\n editor.\n \n\n\n \n \n \n \n Hypersonic Nonequilibrium Flows: Fundamentals and Recent Advances.\n \n \n \n\n\n \n\n\n\n Progress in Astronautics and Aeronautics, 2015.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@book{josyula2015,\n\ttitle = {Hypersonic {Nonequilibrium} {Flows}: {Fundamentals} and {Recent} {Advances}},\n\tpublisher = {Progress in Astronautics and Aeronautics},\n\teditor = {Josyula, Eswar},\n\tyear = {2015},\n}\n\n\n\n
\n
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\n \n\n \n \n Josyula, E.,\n editor.\n \n\n\n \n \n \n \n Hypersonic Nonequilibrium Flows: Fundamentals and Recent Advances.\n \n \n \n\n\n \n\n\n\n AIAA, 2015.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@book{josyula2015b,\n\ttitle = {Hypersonic {Nonequilibrium} {Flows}: {Fundamentals} and {Recent} {Advances}},\n\tpublisher = {AIAA},\n\teditor = {Josyula, Eswar},\n\tyear = {2015},\n}\n\n\n\n
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\n \n\n \n \n Andrienko, D A; and Boyd, I D\n\n\n \n \n \n \n High Fidelity Modeling of Thermal Relaxation and Dissociation of Oxygen.\n \n \n \n\n\n \n\n\n\n Physics of Fluids, 27(11601): 1–25. 2015.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{andrienko2015,\n\ttitle = {High {Fidelity} {Modeling} of {Thermal} {Relaxation} and {Dissociation} of {Oxygen}},\n\tvolume = {27},\n\tnumber = {11601},\n\tjournal = {Physics of Fluids},\n\tauthor = {Andrienko, D A and Boyd, I D},\n\tyear = {2015},\n\tpages = {1--25},\n}\n\n\n\n
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\n \n\n \n \n Juliano, T. J; Adamczak, D.; and Kimmel, R. L\n\n\n \n \n \n \n HIFIRE-5 Flight Test Results.\n \n \n \n\n\n \n\n\n\n Journal of Spacecraft and Rockets, 52(3): 650–663. 2015.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{juliano2015,\n\ttitle = {{HIFIRE}-5 {Flight} {Test} {Results}},\n\tvolume = {52},\n\tdoi = {10.2514/1.A33142},\n\tnumber = {3},\n\tjournal = {Journal of Spacecraft and Rockets},\n\tauthor = {Juliano, Thomas J and Adamczak, David and Kimmel, Roger L},\n\tyear = {2015},\n\tpages = {650--663},\n}\n\n\n\n
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\n \n\n \n \n Ling, J.; and Templeton, J.\n\n\n \n \n \n \n \n Evaluation of machine learning algorithms for prediction of regions of high Reynolds averaged Navier Stokes uncertainty.\n \n \n \n \n\n\n \n\n\n\n Physics of Fluids, 27(8). 2015.\n Publisher: American Institute of Physics Inc.\n\n\n\n
\n\n\n\n \n \n \"EvaluationPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{ling2015,\n\ttitle = {Evaluation of machine learning algorithms for prediction of regions of high {Reynolds} averaged {Navier} {Stokes} uncertainty},\n\tvolume = {27},\n\turl = {http://aip.scitation.org/doi/10.1063/1.4927765},\n\tdoi = {10.1063/1.4927765},\n\tabstract = {Reynolds Averaged Navier Stokes (RANS) models are widely used in industry to predict fluid flows, despite their acknowledged deficiencies. Not only do RANS models often produce inaccurate flow predictions, but there are very limited diagnostics available to assess RANS accuracy for a given flow configuration. If experimental or higher fidelity simulation results are not available for RANS validation, there is no reliable method to evaluate RANS accuracy. This paper explores the potential of utilizing machine learning algorithms to identify regions of high RANS uncertainty. Three different machine learning algorithms were evaluated: support vector machines, Adaboost decision trees, and random forests. The algorithms were trained on a database of canonical flow configurations for which validated direct numerical simulation or large eddy simulation results were available, and were used to classify RANS results on a point-by-point basis as having either high or low uncertainty, based on the breakdown of specific RANS modeling assumptions. Classifiers were developed for three different basic RANS eddy viscosity model assumptions: the isotropy of the eddy viscosity, the linearity of the Boussinesq hypothesis, and the non-negativity of the eddy viscosity. It is shown that these classifiers are able to generalize to flows substantially different from those on which they were trained. Feature selection techniques, model evaluation, and extrapolation detection are discussed in the context of turbulence modeling applications.},\n\tnumber = {8},\n\tjournal = {Physics of Fluids},\n\tauthor = {Ling, J. and Templeton, J.},\n\tyear = {2015},\n\tnote = {Publisher: American Institute of Physics Inc.},\n\tkeywords = {Navier-Stokes equations, decision trees, extrapolation, feature selection, flow simulation, learning (artificial intelligence), support vector machines, turbulence, viscosity},\n}\n\n\n\n
\n
\n\n\n
\n Reynolds Averaged Navier Stokes (RANS) models are widely used in industry to predict fluid flows, despite their acknowledged deficiencies. Not only do RANS models often produce inaccurate flow predictions, but there are very limited diagnostics available to assess RANS accuracy for a given flow configuration. If experimental or higher fidelity simulation results are not available for RANS validation, there is no reliable method to evaluate RANS accuracy. This paper explores the potential of utilizing machine learning algorithms to identify regions of high RANS uncertainty. Three different machine learning algorithms were evaluated: support vector machines, Adaboost decision trees, and random forests. The algorithms were trained on a database of canonical flow configurations for which validated direct numerical simulation or large eddy simulation results were available, and were used to classify RANS results on a point-by-point basis as having either high or low uncertainty, based on the breakdown of specific RANS modeling assumptions. Classifiers were developed for three different basic RANS eddy viscosity model assumptions: the isotropy of the eddy viscosity, the linearity of the Boussinesq hypothesis, and the non-negativity of the eddy viscosity. It is shown that these classifiers are able to generalize to flows substantially different from those on which they were trained. Feature selection techniques, model evaluation, and extrapolation detection are discussed in the context of turbulence modeling applications.\n
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\n \n\n \n \n Uribarri, L. A; and Allen, E. H\n\n\n \n \n \n \n Electron Transpiration Cooling for Hot Aerospace Surfaces.\n \n \n \n\n\n \n\n\n\n In Glasgow, Scotland, July 2015. \\AIAA Paper\\ 2015-3674\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n\n\n\n
\n 
@inproceedings{uribarri2015,\n\taddress = {Glasgow, Scotland},\n\ttitle = {Electron {Transpiration} {Cooling} for {Hot} {Aerospace} {Surfaces}},\n\tpublisher = {\\{AIAA Paper\\} 2015-3674},\n\tauthor = {Uribarri, Luke A and Allen, Edward H},\n\tmonth = jul,\n\tyear = {2015},\n\tkeywords = {etc},\n}\n\n\n\n
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\n \n\n \n \n Hanquist, K. M.; and Boyd, I. D.\n\n\n \n \n \n \n Comparisons of computations with experiments for electron transpiration cooling at high enthalpies.\n \n \n \n\n\n \n\n\n\n In 45th AIAA Thermophysics Conference, pages 1–13, 2015. AIAA Paper 2015-2351\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@inproceedings{hanquist2015b,\n\ttitle = {Comparisons of computations with experiments for electron transpiration cooling at high enthalpies},\n\tdoi = {10.2514/6.2015-2351},\n\tabstract = {A modeling approach for electron transpiration cooling of high enthalpy ight is compared to a set of experiments performed in a plasma arc tunnel for nitrogen and argon. The comparisons include nitrogen and argon ow at high enthalpies, 12,000 btu/lb and 5,000 btu/lb respectively, with a Mach number of 2.5 to 3. Converting the provided enthalpies and Mach numbers to freestream temperatures and velocities is discussed. The numerical approach is described including implementation of a thermionic emission boundary condition. Also described is the implementation of a finite-rate chemistry model for argon ionization. Different emissive materials are also investigated including graphite and tungsten. The comparisons include two different geometries with different leading edge radii. The numerical results produce a wide range of emitted current due to the uncertainties in freestream conditions and emissive material properties, but still agree well with the experiments. Future work recommendations are provided that may improve the physical accuracy of the modeling capabilities used in the comparisons.},\n\tbooktitle = {45th {AIAA} {Thermophysics} {Conference}},\n\tpublisher = {AIAA Paper 2015-2351},\n\tauthor = {Hanquist, Kyle M. and Boyd, Iain D.},\n\tyear = {2015},\n\tkeywords = {etc, own, ★},\n\tpages = {1--13},\n}\n\n\n\n
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\n\n\n
\n A modeling approach for electron transpiration cooling of high enthalpy ight is compared to a set of experiments performed in a plasma arc tunnel for nitrogen and argon. The comparisons include nitrogen and argon ow at high enthalpies, 12,000 btu/lb and 5,000 btu/lb respectively, with a Mach number of 2.5 to 3. Converting the provided enthalpies and Mach numbers to freestream temperatures and velocities is discussed. The numerical approach is described including implementation of a thermionic emission boundary condition. Also described is the implementation of a finite-rate chemistry model for argon ionization. Different emissive materials are also investigated including graphite and tungsten. The comparisons include two different geometries with different leading edge radii. The numerical results produce a wide range of emitted current due to the uncertainties in freestream conditions and emissive material properties, but still agree well with the experiments. Future work recommendations are provided that may improve the physical accuracy of the modeling capabilities used in the comparisons.\n
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\n \n\n \n \n Omidy, A. D; Panerai, F.; Martin, A.; Lachaud, J. R; Cozmuta, I.; and Mansour, N. N\n\n\n \n \n \n \n Code-to-Code Comparison, and Material Response Modeling of Stardust and MSL using PATO and FIAT.\n \n \n \n\n\n \n\n\n\n Technical Report 2015.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@techreport{omidy2015,\n\ttitle = {Code-to-{Code} {Comparison}, and {Material} {Response} {Modeling} of {Stardust} and {MSL} using {PATO} and {FIAT}},\n\tauthor = {Omidy, Ali D and Panerai, Francesco and Martin, Alexandre and Lachaud, Jean R and Cozmuta, Ioana and Mansour, Nagi N},\n\tyear = {2015},\n}\n\n\n\n
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\n \n\n \n \n Bender, J. D; Valentini, P.; Nompelis, I.; Paukku, Y.; Varga, Z.; Truhlar, D. G; Schwartzentruber, T. E; and Candler, G. V\n\n\n \n \n \n \n An improved potential energy surface and multi-temperature quasiclassical trajectory calculations of \\N\\textsubscript\\2\\ + N\\textsubscript\\2\\\\ dissociation reactions.\n \n \n \n\n\n \n\n\n\n The Journal of Chemical Physics, 143(5). 2015.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{bender2015,\n\ttitle = {An improved potential energy surface and multi-temperature quasiclassical trajectory calculations of \\{{N}{\\textbackslash}textsubscript\\{2\\} + {N}{\\textbackslash}textsubscript\\{2\\}\\} dissociation reactions},\n\tvolume = {143},\n\tdoi = {10.1063/1.4927571},\n\tnumber = {5},\n\tjournal = {The Journal of Chemical Physics},\n\tauthor = {Bender, Jason D and Valentini, Paolo and Nompelis, Ioannis and Paukku, Yuliya and Varga, Zoltan and Truhlar, Donald G and Schwartzentruber, Thomas E and Candler, Graham V},\n\tyear = {2015},\n}\n\n\n\n
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\n \n\n \n \n Ferlauto, M.\n\n\n \n \n \n \n A Pseudo-Compressibility Method for Solving Inverse Problems based on the 3D Incompressible Euler Equations.\n \n \n \n\n\n \n\n\n\n Inverse Problems in Science and Engineering. 2015.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@article{ferlauto2015,\n\ttitle = {A {Pseudo}-{Compressibility} {Method} for {Solving} {Inverse} {Problems} based on the {3D} {Incompressible} {Euler} {Equations}},\n\tjournal = {Inverse Problems in Science and Engineering},\n\tauthor = {Ferlauto, M.},\n\tyear = {2015},\n}\n\n\n\n
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\n \n\n \n \n Rand, L P; and Williams, J D\n\n\n \n \n \n \n A Calcium Aluminate Electride Hollow Cathode.\n \n \n \n\n\n \n\n\n\n IEEE Transactions on Plasma Science, 43(1): 190–194. 2015.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@article{rand2015,\n\ttitle = {A {Calcium} {Aluminate} {Electride} {Hollow} {Cathode}},\n\tvolume = {43},\n\tnumber = {1},\n\tjournal = {IEEE Transactions on Plasma Science},\n\tauthor = {Rand, L P and Williams, J D},\n\tyear = {2015},\n\tpages = {190--194},\n}\n\n\n\n
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\n  \n 2014\n \n \n (26)\n \n \n
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\n \n\n \n \n Kim, J G; and Boyd, I D\n\n\n \n \n \n \n Thermochemical nonequilibrium analysis of O$_{\\textrm{2}}$-Ar based on state-resolved kinetics.\n \n \n \n\n\n \n\n\n\n Chemical Physics, 446: 76–85. 2014.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{kim2014,\n\ttitle = {Thermochemical nonequilibrium analysis of {O}$_{\\textrm{2}}$-{Ar} based on state-resolved kinetics},\n\tvolume = {446},\n\tjournal = {Chemical Physics},\n\tauthor = {Kim, J G and Boyd, I D},\n\tyear = {2014},\n\tpages = {76--85},\n}\n\n\n\n
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\n \n\n \n \n Groves, C. E.; Ilie, M.; and Schallhorn, P.\n\n\n \n \n \n \n Computational Fluid Dynamics Uncertainty Analysis for Payload Fairing Spacecraft Environmental Control Systems.\n \n \n \n\n\n \n\n\n\n In 52nd Aerospace Sciences Meeting, National Harbor, Maryland, January 2014. AIAA Paper 2014-0440\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{groves2014a,\n\taddress = {National Harbor, Maryland},\n\ttitle = {Computational {Fluid} {Dynamics} {Uncertainty} {Analysis} for {Payload} {Fairing} {Spacecraft} {Environmental} {Control} {Systems}},\n\tdoi = {10.2514/6.2014-0440},\n\tlanguage = {en},\n\turldate = {2024-04-01},\n\tbooktitle = {52nd {Aerospace} {Sciences} {Meeting}},\n\tpublisher = {AIAA Paper 2014-0440},\n\tauthor = {Groves, Curtis E. and Ilie, Marcel and Schallhorn, Paul},\n\tmonth = jan,\n\tyear = {2014},\n}\n\n\n\n\n\n\n\n
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\n \n\n \n \n Groves, C. E.\n\n\n \n \n \n \n Computational Fluid Dynamics Uncertainty Analysis for Payload Fairing Spacecraft Environmental Control Systems.\n \n \n \n\n\n \n\n\n\n Ph.D. Thesis, University of Central Florida, Orlando, 2014.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@phdthesis{groves2014,\n\taddress = {Orlando},\n\ttitle = {Computational {Fluid} {Dynamics} {Uncertainty} {Analysis} for {Payload} {Fairing} {Spacecraft} {Environmental} {Control} {Systems}},\n\tlanguage = {en},\n\turldate = {2024-03-27},\n\tschool = {University of Central Florida},\n\tauthor = {Groves, Curtis E.},\n\tyear = {2014},\n}\n\n\n\n\n\n\n\n
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\n \n\n \n \n Bansal, N. P; and Lamon, J.\n\n\n \n \n \n \n Ceramic matrix composites: materials, modeling and technology.\n \n \n \n\n\n \n\n\n\n John Wiley & Sons, 2014.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@book{bansal2014ceramic,\n\ttitle = {Ceramic matrix composites: materials, modeling and technology},\n\tpublisher = {John Wiley \\& Sons},\n\tauthor = {Bansal, Narottam P and Lamon, Jacques},\n\tyear = {2014},\n}\n\n\n\n\n\n\n\n\n\n\n\n
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\n \n\n \n \n Wiebenga, J.\n\n\n \n \n \n \n High-Fidelity Material Response Modeling as Part of an Aerothermoelastic Framework for Hypersonic Flows.\n \n \n \n\n\n \n\n\n\n Ph.D. Thesis, University of Michigan, Ann Arbor, 2014.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@phdthesis{wiebenga2014,\n\taddress = {Ann Arbor},\n\ttitle = {High-{Fidelity} {Material} {Response} {Modeling} as {Part} of an {Aerothermoelastic} {Framework} for {Hypersonic} {Flows}},\n\tschool = {University of Michigan},\n\tauthor = {Wiebenga, Jonathan},\n\tyear = {2014},\n}\n\n\n\n
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\n \n\n \n \n Lamorte, N.; Friedmann, P. P.; Glaz, B.; Culler, A. J.; Crowell, A. R.; and McNamara, J. J.\n\n\n \n \n \n \n Uncertainty Propagation in Hypersonic Aerothermoelastic Analysis.\n \n \n \n\n\n \n\n\n\n Journal of Aircraft, 51(1): 192–203. 2014.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{lamorte2014,\n\ttitle = {Uncertainty {Propagation} in {Hypersonic} {Aerothermoelastic} {Analysis}},\n\tvolume = {51},\n\tissn = {0021-8669},\n\tdoi = {10.2514/1.C032233},\n\tabstract = {A framework for uncertainty propagation in hypersonic aeroelastic and aerothermoelastic analyses is presented. First, the aeroelastic stability of a typical section representative of a control surface on a hypersonic vehicle is examined. Variability in the uncoupled natural frequencies of the system is modeled using beta probability distributions. Uncertainty in the flutter Mach number is computed using stochastic collocation. Next, the stability of an aerodynamically heated panel representing a component of the skin of a hypersonic vehicle is considered. In this case, uncertainty is due to the location of transition from laminar to turbulent flow and the heat flux prediction. The effect of propagating these uncertainties on vehicle behavior is determined. For both cases, uncertainty is treated using stochastic collocation, which is a new and effective approach for incorporating uncertainty in this class of problems.},\n\tnumber = {1},\n\turldate = {2023-08-03},\n\tjournal = {Journal of Aircraft},\n\tauthor = {Lamorte, Nicolas and Friedmann, Peretz P. and Glaz, Bryan and Culler, Adam J. and Crowell, Andrew R. and McNamara, Jack J.},\n\tyear = {2014},\n\tpages = {192--203},\n}\n\n\n\n\n\n\n\n\n\n\n\n
\n
\n\n\n
\n A framework for uncertainty propagation in hypersonic aeroelastic and aerothermoelastic analyses is presented. First, the aeroelastic stability of a typical section representative of a control surface on a hypersonic vehicle is examined. Variability in the uncoupled natural frequencies of the system is modeled using beta probability distributions. Uncertainty in the flutter Mach number is computed using stochastic collocation. Next, the stability of an aerodynamically heated panel representing a component of the skin of a hypersonic vehicle is considered. In this case, uncertainty is due to the location of transition from laminar to turbulent flow and the heat flux prediction. The effect of propagating these uncertainties on vehicle behavior is determined. For both cases, uncertainty is treated using stochastic collocation, which is a new and effective approach for incorporating uncertainty in this class of problems.\n
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\n \n\n \n \n Nemec, M.; and Aftosmis, M. J\n\n\n \n \n \n \n \n Toward Automatic Verification of Goal-Oriented Flow Simulations.\n \n \n \n \n\n\n \n\n\n\n Technical Report 2014.\n \n\n\n\n
\n\n\n\n \n \n \"TowardPaper\n  \n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@techreport{nemec2014,\n\ttitle = {Toward {Automatic} {Verification} of {Goal}-{Oriented} {Flow} {Simulations}},\n\turl = {https://ntrs.nasa.gov/citations/20150000864},\n\tauthor = {Nemec, Marian and Aftosmis, Michael J},\n\tyear = {2014},\n}\n\n\n\n
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\n \n\n \n \n Nemec, M.; and Aftosmis, M. J\n\n\n \n \n \n \n \n Toward Automatic Verification of Goal-Oriented Flow Simulations.\n \n \n \n \n\n\n \n\n\n\n Technical Report 2014.\n \n\n\n\n
\n\n\n\n \n \n \"TowardPaper\n  \n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@techreport{nemec2014a,\n\ttitle = {Toward {Automatic} {Verification} of {Goal}-{Oriented} {Flow} {Simulations}},\n\turl = {https://ntrs.nasa.gov/citations/20150000864},\n\tauthor = {Nemec, Marian and Aftosmis, Michael J},\n\tyear = {2014},\n}\n\n\n\n
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\n \n\n \n \n Maglieri, D. J; Bobbitt, P. J; Plotkin, K. J; Shepherd, K. P; Coen, P. G; and Richwine, D. M\n\n\n \n \n \n \n \n Sonic Boom: Six Decades of Research.\n \n \n \n \n\n\n \n\n\n\n Technical Report 2014.\n \n\n\n\n
\n\n\n\n \n \n \"SonicPaper\n  \n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@techreport{maglieri2014,\n\ttitle = {Sonic {Boom}: {Six} {Decades} of {Research}},\n\turl = {https://ntrs.nasa.gov/citations/20150006843},\n\tauthor = {Maglieri, Domenic J and Bobbitt, Percy J and Plotkin, Kenneth J and Shepherd, Kevin P and Coen, Peter G and Richwine, David M},\n\tyear = {2014},\n}\n\n\n\n
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\n \n\n \n \n Lachaud, J.; and Mansour, N. N.\n\n\n \n \n \n \n \n Porous-material analysis toolbox based on openfoam and applications.\n \n \n \n \n\n\n \n\n\n\n In volume 28, pages 191–202, April 2014. American Institute of Aeronautics and Astronautics Inc.\n Issue: 2\n\n\n\n
\n\n\n\n \n \n \"Porous-materialPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@inproceedings{lachaud2014,\n\ttitle = {Porous-material analysis toolbox based on openfoam and applications},\n\tvolume = {28},\n\turl = {http://arc.aiaa.org},\n\tdoi = {10.2514/1.T4262},\n\tabstract = {The Porous-material Analysis Toolbox based on OpenFOAM is a fully portable OpenFOAM library. It isimplemented to test innovative multiscale physics-based models for reacting porous materials that undergo recession.Current developments are focused on ablative materials. The ablative material response module implemented in the Porous-material Analysis Toolbox relies on an original high-fidelity ablation model. The governing equations are volume-averaged forms of the conservation equations for gas mass, gas species, solid mass, gas momentum, and total energy. It may also simply be used as a state-of-the-art ablation model when the right model options are chosen. As applications, three physical analyses are presented: 1) volume-averaged study of the oxidation of a carbon-fiber preform under dry air, 2) three-dimensional analysis of the pyrolysis gas flow in a porous ablative material sample facing an arcjet, and 3) comparison of a state-of-the-art and a high-fidelity model for the thermal and chemical response of a carbon/phenolic ablative material. © 2013 by the American Institute of Aeronautics and Astronautics, Inc.},\n\tpublisher = {American Institute of Aeronautics and Astronautics Inc.},\n\tauthor = {Lachaud, Jean and Mansour, Nagi N.},\n\tmonth = apr,\n\tyear = {2014},\n\tnote = {Issue: 2},\n\tkeywords = {Ablative Materials, Chemical Equilibrium, Conservation Equations, Conservation of Mass, Convective Boundary Condition, Diffusion Coefficient, Energy Transfer, Forced Convection, Porous Materials, Pyrolysis Gas Flow},\n\tpages = {191--202},\n}\n\n\n\n
\n
\n\n\n
\n The Porous-material Analysis Toolbox based on OpenFOAM is a fully portable OpenFOAM library. It isimplemented to test innovative multiscale physics-based models for reacting porous materials that undergo recession.Current developments are focused on ablative materials. The ablative material response module implemented in the Porous-material Analysis Toolbox relies on an original high-fidelity ablation model. The governing equations are volume-averaged forms of the conservation equations for gas mass, gas species, solid mass, gas momentum, and total energy. It may also simply be used as a state-of-the-art ablation model when the right model options are chosen. As applications, three physical analyses are presented: 1) volume-averaged study of the oxidation of a carbon-fiber preform under dry air, 2) three-dimensional analysis of the pyrolysis gas flow in a porous ablative material sample facing an arcjet, and 3) comparison of a state-of-the-art and a high-fidelity model for the thermal and chemical response of a carbon/phenolic ablative material. © 2013 by the American Institute of Aeronautics and Astronautics, Inc.\n
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\n \n\n \n \n Martin, A.; and Boyd, I. D\n\n\n \n \n \n \n \n Modeling of Heat Transfer Attenuation by Ablative Gases During the Stardust Reentry.\n \n \n \n \n\n\n \n\n\n\n Journal of Thermophysics and Heat Transfer, 29(3). 2014.\n \n\n\n\n
\n\n\n\n \n \n \"ModelingPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{martin2014,\n\ttitle = {Modeling of {Heat} {Transfer} {Attenuation} by {Ablative} {Gases} {During} the {Stardust} {Reentry}},\n\tvolume = {29},\n\turl = {http://arc.aiaa.org},\n\tdoi = {10.2514/1.T4202},\n\tabstract = {Modern space vehicles designed for planetary exploration use ablative materials to protect the payload against the high heating environment experienced during reentry. To properly model and predict the aerothermal environment of the vehicle, it is imperative to account for the gases produced by ablation processes. The present study aims to examine the effects of the blowing of ablation gas in the outer flow field. Using six points on the Stardust entry trajectory at the beginning of the continuum regime, from 81 to 69 km, the various components of the heat flux are compared to air-only solutions. Although an additional component of the heat flux is introduced by mass diffusion, this additional term is mainly balanced by the fact that the translational-rotational component of the heat flux, the main contributor, is greatly reduced. Although a displacement of the shock is observed, it is believed that the most prominent effects are caused by a modification of the chemical composition of the boundary layer, which reduces the gas-phase thermal conductivity. Nomenclature B 0 = nondimensional ablation rate C = vector of source terms D = mass diffusion coefficient, m 2 ∕s E = energy, J∕m 3 e = energy, J∕kg F = inviscid flux matrix F d = diffusive flux matrix h = species enthalpy vector, J∕kg I = identity matrix J = directional species diffusion, kg∕m 2 · s† Kn = Knudsen number k = thermal conductivity, W∕m · K† \\_ m 0 0 = mass flow rate, kg∕m 2 · s† p = pressure, Pa Q = vector of conserved variables q = heat flux, W∕m 2 T = temperature, K U, v = velocity, m∕s \\_ w = mass source term, kg∕m 3 · s† \\_ w v = vibrational energy relaxation source term, J∕m 3 · s† Y = mass fraction, kg∕kg η = distance normal to the wall, m ρ = mass density, kg∕m 3 τ = viscous tensor, Pa Subscripts c = char g = gas blown nc = next to the wall s = species t = time tr = translational-rotational ve = vibrational-electron-electronic w = wall ∞ = freestream},\n\tnumber = {3},\n\tjournal = {Journal of Thermophysics and Heat Transfer},\n\tauthor = {Martin, Alexandre and Boyd, Iain D},\n\tyear = {2014},\n}\n\n\n\n
\n
\n\n\n
\n Modern space vehicles designed for planetary exploration use ablative materials to protect the payload against the high heating environment experienced during reentry. To properly model and predict the aerothermal environment of the vehicle, it is imperative to account for the gases produced by ablation processes. The present study aims to examine the effects of the blowing of ablation gas in the outer flow field. Using six points on the Stardust entry trajectory at the beginning of the continuum regime, from 81 to 69 km, the various components of the heat flux are compared to air-only solutions. Although an additional component of the heat flux is introduced by mass diffusion, this additional term is mainly balanced by the fact that the translational-rotational component of the heat flux, the main contributor, is greatly reduced. Although a displacement of the shock is observed, it is believed that the most prominent effects are caused by a modification of the chemical composition of the boundary layer, which reduces the gas-phase thermal conductivity. Nomenclature B 0 = nondimensional ablation rate C = vector of source terms D = mass diffusion coefficient, m 2 ∕s E = energy, J∕m 3 e = energy, J∕kg F = inviscid flux matrix F d = diffusive flux matrix h = species enthalpy vector, J∕kg I = identity matrix J = directional species diffusion, kg∕m 2 · s† Kn = Knudsen number k = thermal conductivity, W∕m · K† _ m 0 0 = mass flow rate, kg∕m 2 · s† p = pressure, Pa Q = vector of conserved variables q = heat flux, W∕m 2 T = temperature, K U, v = velocity, m∕s _ w = mass source term, kg∕m 3 · s† _ w v = vibrational energy relaxation source term, J∕m 3 · s† Y = mass fraction, kg∕kg η = distance normal to the wall, m ρ = mass density, kg∕m 3 τ = viscous tensor, Pa Subscripts c = char g = gas blown nc = next to the wall s = species t = time tr = translational-rotational ve = vibrational-electron-electronic w = wall ∞ = freestream\n
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\n \n\n \n \n Rosema, C.; Doyle, J.; and Blake, W. B\n\n\n \n \n \n \n \n MISSILE DATA COMPENDIUM (DATCOM) User Manual-2014 Revision.\n \n \n \n \n\n\n \n\n\n\n Technical Report AFRL-RQ-WP-TR-2014-0281, 2014.\n \n\n\n\n
\n\n\n\n \n \n \"MISSILEPaper\n  \n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@techreport{rosema2014,\n\taddress = {AFRL-RQ-WP-TR-2014-0281},\n\ttitle = {{MISSILE} {DATA} {COMPENDIUM} ({DATCOM}) {User} {Manual}-2014 {Revision}},\n\turl = {http://www.dtic.mil},\n\tauthor = {Rosema, Christopher and Doyle, Joshua and Blake, William B},\n\tyear = {2014},\n}\n\n\n\n
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\n \n\n \n \n Owen, K\n\n\n \n \n \n \n Measurements of Vibrational Relaxation and Dissociation of Oxygen with Laser Absorption Spectroscopy with Applications for Energy Transfer in Nonequilibrium Air.\n \n \n \n\n\n \n\n\n\n . 2014.\n Place: Stanford\n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@article{owen2014,\n\ttitle = {Measurements of {Vibrational} {Relaxation} and {Dissociation} of {Oxygen} with {Laser} {Absorption} {Spectroscopy} with {Applications} for {Energy} {Transfer} in {Nonequilibrium} {Air}},\n\tauthor = {Owen, K},\n\tyear = {2014},\n\tnote = {Place: Stanford},\n}\n\n\n\n
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\n \n\n \n \n Marineau, E. C; Moraru, C G.; Lewis, D. R; Norris, J. D; and Lafferty, J. F\n\n\n \n \n \n \n Mach 10 Boundary-Layer Transition Experiments on Sharp and Blunted Cones.\n \n \n \n\n\n \n\n\n\n In Atlanta, GA, 2014. \\AIAA Paper\\ 2014-3108\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@inproceedings{marineau2014,\n\taddress = {Atlanta, GA},\n\ttitle = {Mach 10 {Boundary}-{Layer} {Transition} {Experiments} on {Sharp} and {Blunted} {Cones}},\n\tpublisher = {\\{AIAA Paper\\} 2014-3108},\n\tauthor = {Marineau, Eric C and Moraru, C George and Lewis, Daniel R and Norris, Joseph D and Lafferty, John F},\n\tyear = {2014},\n}\n\n\n\n
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\n \n\n \n \n Clemens, N. T.; and Narayanaswamy, V.\n\n\n \n \n \n \n Low-Frequency Unsteadiness of Shock Wave/Turbulent Boundary Layer Interactions.\n \n \n \n\n\n \n\n\n\n Annual Review of Fluid Mechanics, 46(1): 469–492. January 2014.\n Publisher: Annual Reviews\n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@article{clemens2014,\n\ttitle = {Low-{Frequency} {Unsteadiness} of {Shock} {Wave}/{Turbulent} {Boundary} {Layer} {Interactions}},\n\tvolume = {46},\n\tissn = {0066-4189},\n\tdoi = {10.1146/annurev-fluid-010313-141346},\n\tabstract = {Shock wave/boundary layer interactions occur in a wide range of supersonic internal and external flows, and often these interactions are associated with turbulent boundary layer separation. The resulting separated flow is associated with large-scale, low-frequency unsteadiness whose cause has been the subject of much attention and debate. In particular, some researchers have concluded that the source of low-frequency motions is in the upstream boundary layer, whereas others have argued for a downstream instability as the driving mechanism. Owing to substantial recent activity, we are close to developing a comprehensive understanding, albeit only in simplified flow configurations. A plausible model is that the interaction responds as a dynamical system that is forced by external disturbances. The low-frequency dynamics seem to be adequately described by a recently proposed shear layer entrainment-recharge mechanism. Upstream boundary layer fluctuations seem to be an important source of disturbances, but the evidence suggests that their impact is reduced with increasing size of the separated flow.},\n\tnumber = {1},\n\turldate = {2023-01-12},\n\tjournal = {Annual Review of Fluid Mechanics},\n\tauthor = {Clemens, Noel T. and Narayanaswamy, Venkateswaran},\n\tmonth = jan,\n\tyear = {2014},\n\tnote = {Publisher: Annual Reviews},\n\tpages = {469--492},\n}\n\n\n\n
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\n Shock wave/boundary layer interactions occur in a wide range of supersonic internal and external flows, and often these interactions are associated with turbulent boundary layer separation. The resulting separated flow is associated with large-scale, low-frequency unsteadiness whose cause has been the subject of much attention and debate. In particular, some researchers have concluded that the source of low-frequency motions is in the upstream boundary layer, whereas others have argued for a downstream instability as the driving mechanism. Owing to substantial recent activity, we are close to developing a comprehensive understanding, albeit only in simplified flow configurations. A plausible model is that the interaction responds as a dynamical system that is forced by external disturbances. The low-frequency dynamics seem to be adequately described by a recently proposed shear layer entrainment-recharge mechanism. Upstream boundary layer fluctuations seem to be an important source of disturbances, but the evidence suggests that their impact is reduced with increasing size of the separated flow.\n
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\n \n\n \n \n Wang, Z. J.\n\n\n \n \n \n \n High-order computational fluid dynamics tools for aircraft design.\n \n \n \n\n\n \n\n\n\n Philosophical Transactions of the Royal Society A: Mathematical, Physical and Engineering Sciences, 372(2022): 20130318. August 2014.\n Publisher: Royal Society\n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{wang2014,\n\ttitle = {High-order computational fluid dynamics tools for aircraft design},\n\tvolume = {372},\n\tdoi = {10.1098/rsta.2013.0318},\n\tnumber = {2022},\n\turldate = {2023-01-12},\n\tjournal = {Philosophical Transactions of the Royal Society A: Mathematical, Physical and Engineering Sciences},\n\tauthor = {Wang, Z. J.},\n\tmonth = aug,\n\tyear = {2014},\n\tnote = {Publisher: Royal Society},\n\tpages = {20130318},\n}\n\n\n\n
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\n \n\n \n \n Deck, S.; Gand, F.; Brunet, V.; and Ben Khelil, S.\n\n\n \n \n \n \n High-fidelity simulations of unsteady civil aircraft aerodynamics: stakes and perspectives. Application of zonal detached eddy simulation.\n \n \n \n\n\n \n\n\n\n Philosophical Transactions of the Royal Society A: Mathematical, Physical and Engineering Sciences, 372(2022): 20130325. August 2014.\n Publisher: Royal Society\n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{deck2014,\n\ttitle = {High-fidelity simulations of unsteady civil aircraft aerodynamics: stakes and perspectives. {Application} of zonal detached eddy simulation},\n\tvolume = {372},\n\tdoi = {10.1098/rsta.2013.0325},\n\tnumber = {2022},\n\turldate = {2023-01-11},\n\tjournal = {Philosophical Transactions of the Royal Society A: Mathematical, Physical and Engineering Sciences},\n\tauthor = {Deck, Sébastien and Gand, Fabien and Brunet, Vincent and Ben Khelil, Saloua},\n\tmonth = aug,\n\tyear = {2014},\n\tnote = {Publisher: Royal Society},\n\tpages = {20130325},\n}\n\n\n\n
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\n \n\n \n \n Gudmundsson, S.\n\n\n \n \n \n \n \n General Aviation Aircraft Design.\n \n \n \n \n\n\n \n\n\n\n Butterworth-Heinemann, 2014.\n \n\n\n\n
\n\n\n\n \n \n \"GeneralPaper\n  \n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@book{gudmundsson2014,\n\ttitle = {General {Aviation} {Aircraft} {Design}},\n\turl = {https://doi.org/10.1016/C2011-0-06824-2},\n\tpublisher = {Butterworth-Heinemann},\n\tauthor = {Gudmundsson, Snorri},\n\tyear = {2014},\n}\n\n\n\n
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\n \n\n \n \n Alkandry, H.; Hanquist, K. M.; and Boyd, I. D.\n\n\n \n \n \n \n Conceptual analysis of electron transpiration cooling for the leading edges of hypersonic vehicles.\n \n \n \n\n\n \n\n\n\n In 11th AIAA/ASME Joint Thermophysics and Heat Transfer Conference, 2014. AIAA Paper 2014-2674\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@inproceedings{alkandry2014b,\n\ttitle = {Conceptual analysis of electron transpiration cooling for the leading edges of hypersonic vehicles},\n\tdoi = {10.2514/6.2014-2674},\n\tabstract = {Recent progress is presented in an ongoing effort to perform a conceptual analysis of possible electron transpiration cooling using thermo-electric materials at the leading edges of hypersonic vehicles. The implementation of a new boundary condition in the CFD code LeMANS to model the thermionic emission of electrons from the leading edges of hypersonic vehicles is described. A parametric study is performed to understand the effects of the material work function, the freestream velocity, and the leading edge geometry on this cooling effect. The numerical results reveal that lower material work functions, higher freestream velocities, and smaller leading edges can increase the cooling effect due to larger emission current densities. The numerical results also show that the electric field produced by the electron emission may not have a significant effect on the predicted properties. Future work recommendations are provided that may improve the physical accuracy of the modeling capabilities used in this study.},\n\tbooktitle = {11th {AIAA}/{ASME} {Joint} {Thermophysics} and {Heat} {Transfer} {Conference}},\n\tpublisher = {AIAA Paper 2014-2674},\n\tauthor = {Alkandry, Hicham and Hanquist, Kyle M. and Boyd, Iain D.},\n\tyear = {2014},\n\tkeywords = {etc, own, ★},\n}\n\n\n\n
\n
\n\n\n
\n Recent progress is presented in an ongoing effort to perform a conceptual analysis of possible electron transpiration cooling using thermo-electric materials at the leading edges of hypersonic vehicles. The implementation of a new boundary condition in the CFD code LeMANS to model the thermionic emission of electrons from the leading edges of hypersonic vehicles is described. A parametric study is performed to understand the effects of the material work function, the freestream velocity, and the leading edge geometry on this cooling effect. The numerical results reveal that lower material work functions, higher freestream velocities, and smaller leading edges can increase the cooling effect due to larger emission current densities. The numerical results also show that the electric field produced by the electron emission may not have a significant effect on the predicted properties. Future work recommendations are provided that may improve the physical accuracy of the modeling capabilities used in this study.\n
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\n \n\n \n \n Adams, B M; Bauman, L E; Bohnhoff, W J; Dalbey, K R; Ebeida, M S; Eddy, J P; Eldred, M S; Hough, P D; Hu, K T; Jakeman, J D; Stephens, J A; Swiler, L P; Vigil, D M; and Wildey, T M\n\n\n \n \n \n \n Dakota, A Multilevel Parallel Object-Oriented Framework for Design Optimization, Parameter Estimation, Uncertainty Quantification, and Sensitivity Analysis: Version 6.0 User's Manual.\n \n \n \n\n\n \n\n\n\n Technical Report 2014.\n Issue: Sandia Technical Report SAND2014-4633\n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@techreport{adams2014,\n\ttitle = {Dakota, {A} {Multilevel} {Parallel} {Object}-{Oriented} {Framework} for {Design} {Optimization}, {Parameter} {Estimation}, {Uncertainty} {Quantification}, and {Sensitivity} {Analysis}: {Version} 6.0 {User}'s {Manual}},\n\tauthor = {Adams, B M and Bauman, L E and Bohnhoff, W J and Dalbey, K R and Ebeida, M S and Eddy, J P and Eldred, M S and Hough, P D and Hu, K T and Jakeman, J D and Stephens, J A and Swiler, L P and Vigil, D M and Wildey, T M},\n\tyear = {2014},\n\tnote = {Issue: Sandia Technical Report SAND2014-4633},\n}\n\n\n\n
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\n \n\n \n \n MacLean, M; Holden, M; and Dufrene, A\n\n\n \n \n \n \n Comparison Between CFD and Measurements for Real-Gas Effects on Laminar Shock Wave Boundary Layer Interaction, 1.\n \n \n \n\n\n \n\n\n\n In 2014. \\AIAA Paper\\ 2014-3366\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{maclean2014,\n\ttitle = {Comparison {Between} {CFD} and {Measurements} for {Real}-{Gas} {Effects} on {Laminar} {Shock} {Wave} {Boundary} {Layer} {Interaction}, 1},\n\tpublisher = {\\{AIAA Paper\\} 2014-3366},\n\tauthor = {MacLean, M and Holden, M and Dufrene, A},\n\tyear = {2014},\n}\n\n\n\n
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\n \n\n \n \n Schoenenberger, M.; Van Norman, J.; Karlgaard, C.; Kutty, P.; and Way, D.\n\n\n \n \n \n \n \n Assessment of the reconstructed aerodynamics of the mars science laboratory entry vehicle.\n \n \n \n \n\n\n \n\n\n\n Journal of Spacecraft and Rockets, 51(4): 1076–1093. August 2014.\n Publisher: American Institute of Aeronautics and Astronautics Inc.\n\n\n\n
\n\n\n\n \n \n \"AssessmentPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{schoenenberger2014,\n\ttitle = {Assessment of the reconstructed aerodynamics of the mars science laboratory entry vehicle},\n\tvolume = {51},\n\turl = {https://arc.aiaa.org/doi/10.2514/1.A32794},\n\tdoi = {10.2514/1.A32794/ASSET/IMAGES/LARGE/FIGURE23.JPEG},\n\tabstract = {On5 August 2012, the Mars Science Laboratory entry vehicle successfully entered the atmosphere of Mars, flying a guided entry until parachute deploy. The Curiosity rover landed safely in Gale crater upon completion of the entry, descent, and landing sequence. Preflight aerodynamic predictions are compared with the aerodynamic performance of the entry capsule identified from onboard flight data, including inertial-measurement-unit accelerometer and rate gyro information, and heat shield surface pressure measurements. From the onboard data, static force and moment coefficients have been extracted. These data are compared with the preflight aerodynamic database. The Mars Science Laboratory flight data represent the most complete and self-consistent record of a blunt capsule entering Mars collected to date. These data enable the separation of aerodynamic performance from atmospheric conditions. The comparisons show the Mars Science Laboratory aerodynamic characteristics have been successfully identified and resolved to an accuracy better than the aerodynamic database uncertainties used in preflight simulations. A number of small anomalies have been identified and are discussed. These data will help improve aerodynamic databases for future missions and will guide computational fluid dynamics development to improve predictions. © 2012 AIAA.},\n\tnumber = {4},\n\tjournal = {Journal of Spacecraft and Rockets},\n\tauthor = {Schoenenberger, Mark and Van Norman, John and Karlgaard, Chris and Kutty, Prasad and Way, David},\n\tmonth = aug,\n\tyear = {2014},\n\tnote = {Publisher: American Institute of Aeronautics and Astronautics Inc.},\n\tkeywords = {Accelerometer, Aerodynamic Angle, Aerodynamic Force Coefficients, Atmospheric Conditions, CFD Analysis, Flight Software, Mars Science Laboratory, Miniature Inertial Measurement Unit, Pressure Coefficient, Thermal Protection System},\n\tpages = {1076--1093},\n}\n\n\n\n
\n
\n\n\n
\n On5 August 2012, the Mars Science Laboratory entry vehicle successfully entered the atmosphere of Mars, flying a guided entry until parachute deploy. The Curiosity rover landed safely in Gale crater upon completion of the entry, descent, and landing sequence. Preflight aerodynamic predictions are compared with the aerodynamic performance of the entry capsule identified from onboard flight data, including inertial-measurement-unit accelerometer and rate gyro information, and heat shield surface pressure measurements. From the onboard data, static force and moment coefficients have been extracted. These data are compared with the preflight aerodynamic database. The Mars Science Laboratory flight data represent the most complete and self-consistent record of a blunt capsule entering Mars collected to date. These data enable the separation of aerodynamic performance from atmospheric conditions. The comparisons show the Mars Science Laboratory aerodynamic characteristics have been successfully identified and resolved to an accuracy better than the aerodynamic database uncertainties used in preflight simulations. A number of small anomalies have been identified and are discussed. These data will help improve aerodynamic databases for future missions and will guide computational fluid dynamics development to improve predictions. © 2012 AIAA.\n
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\n \n\n \n \n Jewell, J. S\n\n\n \n \n \n \n Boundary-Layer Transition on a Slender Cone in Hypervelocity Flow with Real Gas Effects.\n \n \n \n\n\n \n\n\n\n Ph.D. Thesis, California Institute of Technology, 2014.\n \n\n\n\n
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@phdthesis{jewell2014b,\n\ttitle = {Boundary-{Layer} {Transition} on a {Slender} {Cone} in {Hypervelocity} {Flow} with {Real} {Gas} {Effects}},\n\tschool = {California Institute of Technology},\n\tauthor = {Jewell, Joseph S},\n\tyear = {2014},\n}\n\n\n\n
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\n \n\n \n \n Jewell, J. S\n\n\n \n \n \n \n Boundary-Layer Transition on a Slender Cone in Hypervelocity Flow with Real Gas Effects.\n \n \n \n\n\n \n\n\n\n . 2014.\n \n\n\n\n
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@article{jewell2014a,\n\ttitle = {Boundary-{Layer} {Transition} on a {Slender} {Cone} in {Hypervelocity} {Flow} with {Real} {Gas} {Effects}},\n\tauthor = {Jewell, Joseph S},\n\tyear = {2014},\n}\n\n\n\n
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\n \n\n \n \n Jewell, J. S\n\n\n \n \n \n \n Boundary-Layer Transition on a Slender Cone in Hypervelocity Flow with Real Gas Effects.\n \n \n \n\n\n \n\n\n\n . May 2014.\n Place: Pasadena, CA\n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@article{jewell2014,\n\ttitle = {Boundary-{Layer} {Transition} on a {Slender} {Cone} in {Hypervelocity} {Flow} with {Real} {Gas} {Effects}},\n\tauthor = {Jewell, Joseph S},\n\tmonth = may,\n\tyear = {2014},\n\tnote = {Place: Pasadena, CA},\n}\n\n\n\n
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\n \n\n \n \n Vogiatzis, K.; Boyer, C.; Wei, K.; Tang, J.; and Ellerbroek, B.\n\n\n \n \n \n \n Aero-thermal simulations of the TMT Laser Guide Star Facility.\n \n \n \n\n\n \n\n\n\n In Marchetti, E.; Close, L. M; and Véran, J., editor(s), volume 9148, pages 2024–2033, Montreal, Quebec, August 2014. SPIE\n \n\n\n\n
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@inproceedings{vogiatzis2014,\n\taddress = {Montreal, Quebec},\n\ttitle = {Aero-thermal simulations of the {TMT} {Laser} {Guide} {Star} {Facility}},\n\tvolume = {9148},\n\tpublisher = {SPIE},\n\tauthor = {Vogiatzis, Konstantinos and Boyer, Corinne and Wei, Kai and Tang, Jinlong and Ellerbroek, Brent},\n\teditor = {Marchetti, Enrico and Close, Laird M and Véran, Jean-Pierre},\n\tmonth = aug,\n\tyear = {2014},\n\tpages = {2024--2033},\n}\n\n\n\n
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\n  \n 2013\n \n \n (15)\n \n \n
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\n \n\n \n \n \n\n\n \n \n \n \n \n Delta IV Launch Services User's Guide.\n \n \n \n \n\n\n \n\n\n\n June 2013.\n \n\n\n\n
\n\n\n\n \n \n \"DeltaPaper\n  \n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@misc{delta2013,\n\ttitle = {Delta {IV} {Launch} {Services} {User}'s {Guide}},\n\turl = {https://www.ulalaunch.com/docs/default-source/rockets/delta-iv-user's-guide.pdf},\n\tmonth = jun,\n\tyear = {2013},\n}\n\n\n\n
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\n \n\n \n \n Kim, J G; and Boyd, I D\n\n\n \n \n \n \n State-Resolved Master Equation Analysis of Thermochemical Nonequilibrium of Nitrogen.\n \n \n \n\n\n \n\n\n\n Chemical Physics, 415(3): 237–246. 2013.\n \n\n\n\n
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@article{kim2013,\n\ttitle = {State-{Resolved} {Master} {Equation} {Analysis} of {Thermochemical} {Nonequilibrium} of {Nitrogen}},\n\tvolume = {415},\n\tdoi = {10.1016/j.chemphys.2013.01.027},\n\tnumber = {3},\n\tjournal = {Chemical Physics},\n\tauthor = {Kim, J G and Boyd, I D},\n\tyear = {2013},\n\tpages = {237--246},\n}\n\n\n\n
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\n \n\n \n \n Bijl, H.; Lucor, D.; Mishra, S.; and Schwab, C.\n\n\n \n \n \n \n Uncertainty Quantification in Computational Fluid Dynamics.\n \n \n \n\n\n \n\n\n\n Springer, 2013.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@book{bijl2013,\n\ttitle = {Uncertainty {Quantification} in {Computational} {Fluid} {Dynamics}},\n\tisbn = {978-3-319-00884-4},\n\tlanguage = {English},\n\tpublisher = {Springer},\n\tauthor = {Bijl, Hester and Lucor, Didier and Mishra, Siddhartha and Schwab, Christoph},\n\tyear = {2013},\n}\n\n\n\n
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\n \n\n \n \n Lamorte, N.\n\n\n \n \n \n \n Uncertainty Propagation in Hypersonic Vehicle Aerothermoelastic Analysis.\n \n \n \n\n\n \n\n\n\n Ph.D. Thesis, University of Michigan, Ann Arbor, 2013.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@phdthesis{lamorte2013,\n\taddress = {Ann Arbor},\n\ttitle = {Uncertainty {Propagation} in {Hypersonic} {Vehicle} {Aerothermoelastic} {Analysis}},\n\tschool = {University of Michigan},\n\tauthor = {Lamorte, Nicolas},\n\tyear = {2013},\n}\n\n\n\n
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\n \n\n \n \n Rondeau, C. M; and Jorris, T. R\n\n\n \n \n \n \n X-51A Scramjet Demostrator Program: Waverider Ground and Flight Test,.\n \n \n \n\n\n \n\n\n\n In pages 1–14, 2013. \n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@inproceedings{rondeau2013,\n\ttitle = {X-{51A} {Scramjet} {Demostrator} {Program}: {Waverider} {Ground} and {Flight} {Test},},\n\tauthor = {Rondeau, Christopher M and Jorris, Timothy R},\n\tyear = {2013},\n\tpages = {1--14},\n}\n\n\n\n
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\n \n\n \n \n Robertson, S.\n\n\n \n \n \n \n Sheaths in laboratory and space plasmas.\n \n \n \n\n\n \n\n\n\n Plasma Physics and Controlled Fusion, 55(9). July 2013.\n Publisher: IOP Publishing\n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@article{robertson2013,\n\ttitle = {Sheaths in laboratory and space plasmas},\n\tvolume = {55},\n\tdoi = {10.1088/0741-3335/55/9/093001},\n\tabstract = {The sheaths that occur at surfaces in laboratory and space plasmas are reviewed with an emphasis on numerical models that can be solved with modest computational resources. The surfaces in plasma may be the interior walls of confinement devices or inserted probes. Fluid and kinetic models are presented in some detail, and particle-in-cell models are discussed briefly. The numerical methods find the spatial profile of the potential, the particle densities near the surfaces and the current to the surfaces. Maxwellian electrons and cold ions are assumed at the outset and subsequently the models are expanded to encompass (1) multiple electron populations, (2) multiple ion species, (3) finite ion temperature, (4) surfaces that emit electrons such as heated cathodes or emissive probes and (5) surfaces that emit plasma as in the Q-machine. These complications may produce nonmonotonic sheaths in which the first derivative of the potential changes sign or double layers in which the second derivative changes sign. The effect of charge-exchange collisions on ion losses to the wall and on ion current to probes is discussed, but models with collisions of electron are omitted. Some recent advances are discussed, including experiments that measure the ion distribution function in sheaths using laser-induced fluorescence, experiments and numerical models on sheaths with multiple ion species and computational models of sheaths surrounding objects in flowing plasma. © 2013 IOP Publishing Ltd.},\n\tnumber = {9},\n\tjournal = {Plasma Physics and Controlled Fusion},\n\tauthor = {Robertson, Scott},\n\tmonth = jul,\n\tyear = {2013},\n\tnote = {Publisher: IOP Publishing},\n}\n\n\n\n
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\n The sheaths that occur at surfaces in laboratory and space plasmas are reviewed with an emphasis on numerical models that can be solved with modest computational resources. The surfaces in plasma may be the interior walls of confinement devices or inserted probes. Fluid and kinetic models are presented in some detail, and particle-in-cell models are discussed briefly. The numerical methods find the spatial profile of the potential, the particle densities near the surfaces and the current to the surfaces. Maxwellian electrons and cold ions are assumed at the outset and subsequently the models are expanded to encompass (1) multiple electron populations, (2) multiple ion species, (3) finite ion temperature, (4) surfaces that emit electrons such as heated cathodes or emissive probes and (5) surfaces that emit plasma as in the Q-machine. These complications may produce nonmonotonic sheaths in which the first derivative of the potential changes sign or double layers in which the second derivative changes sign. The effect of charge-exchange collisions on ion losses to the wall and on ion current to probes is discussed, but models with collisions of electron are omitted. Some recent advances are discussed, including experiments that measure the ion distribution function in sheaths using laser-induced fluorescence, experiments and numerical models on sheaths with multiple ion species and computational models of sheaths surrounding objects in flowing plasma. © 2013 IOP Publishing Ltd.\n
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\n \n\n \n \n Farbar, E.; Boyd, I. D; and Martin, A.\n\n\n \n \n \n \n Numerical Prediction of Hypersonic Flowfields Including Effects of Electron Translational Nonequilibrium.\n \n \n \n\n\n \n\n\n\n Journal of Thermophysics and Heat Transfer, 27(4): 593–606. 2013.\n \n\n\n\n
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\n 
@article{farbar2013,\n\ttitle = {Numerical {Prediction} of {Hypersonic} {Flowfields} {Including} {Effects} of {Electron} {Translational} {Nonequilibrium}},\n\tvolume = {27},\n\tnumber = {4},\n\tjournal = {Journal of Thermophysics and Heat Transfer},\n\tauthor = {Farbar, Erin and Boyd, Iain D and Martin, Alexandre},\n\tyear = {2013},\n\tpages = {593--606},\n}\n\n\n\n
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\n \n\n \n \n Martins, J. R.; and Lambe, A. B.\n\n\n \n \n \n \n \n Multidisciplinary design optimization: A survey of architectures.\n \n \n \n \n\n\n \n\n\n\n AIAA Journal, 51(9): 2049–2075. September 2013.\n Publisher: American Institute of Aeronautics and Astronautics\n\n\n\n
\n\n\n\n \n \n \"MultidisciplinaryPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{martins2013,\n\ttitle = {Multidisciplinary design optimization: {A} survey of architectures},\n\tvolume = {51},\n\turl = {http://arc.aiaa.org},\n\tdoi = {10.2514/1.J051895},\n\tabstract = {Multidisciplinary design optimization is a field of research that studies the application of numerical optimization techniques to the design of engineering systems involving multiple disciplines or components. Since the inception of multidisciplinary design optimization, various methods (architectures) have been developed and applied to solve multidisciplinary design-optimization problems. This paper provides a survey of all the architectures that have been presented in the literature so far. All architectures are explained in detail using a unified description that includes optimization problem statements, diagrams, and detailed algorithms. The diagrams show both data and process flow through the multidisciplinary system and computational elements, which facilitate the understanding of the various architectures, and how they relate to each other. A classification of the multidisciplinary design-optimization architectures based on their problem formulations and decomposition strategies is also provided, and the benefits and drawbacks of the architectures are discussed from both theoretical and experimental perspectives. For each architecture, several applications to the solution of engineering-design problems are cited. The result is a comprehensive but straightforward introduction to multidisciplinary design optimization for nonspecialists and a reference detailing all current multidisciplinary design-optimization architectures for specialists. Copyright © 2013 by the authors.},\n\tnumber = {9},\n\tjournal = {AIAA Journal},\n\tauthor = {Martins, Joaquim R.R.A. and Lambe, Andrew B.},\n\tmonth = sep,\n\tyear = {2013},\n\tnote = {Publisher: American Institute of Aeronautics and Astronautics},\n\tkeywords = {Aerodynamic Loads, Aircraft Design, Computing, Lagrange Multipliers, MDO, Numerical Optimization, Sequential Linear Programming, Sequential Quadratic Programming, Structural Analysis, Structural Optimization},\n\tpages = {2049--2075},\n}\n\n\n\n
\n
\n\n\n
\n Multidisciplinary design optimization is a field of research that studies the application of numerical optimization techniques to the design of engineering systems involving multiple disciplines or components. Since the inception of multidisciplinary design optimization, various methods (architectures) have been developed and applied to solve multidisciplinary design-optimization problems. This paper provides a survey of all the architectures that have been presented in the literature so far. All architectures are explained in detail using a unified description that includes optimization problem statements, diagrams, and detailed algorithms. The diagrams show both data and process flow through the multidisciplinary system and computational elements, which facilitate the understanding of the various architectures, and how they relate to each other. A classification of the multidisciplinary design-optimization architectures based on their problem formulations and decomposition strategies is also provided, and the benefits and drawbacks of the architectures are discussed from both theoretical and experimental perspectives. For each architecture, several applications to the solution of engineering-design problems are cited. The result is a comprehensive but straightforward introduction to multidisciplinary design optimization for nonspecialists and a reference detailing all current multidisciplinary design-optimization architectures for specialists. Copyright © 2013 by the authors.\n
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\n \n\n \n \n Ibraguimova, L B; Sergievskaya, A L; Levashov, V Y.; Shatalov, O P; Tunik, Y. V; and Zabelinskii, I E\n\n\n \n \n \n \n Investigation of oxygen dissociation and vibrational relaxation at temperatures 4000–10 800 K.\n \n \n \n\n\n \n\n\n\n The Journal of Chemical Physics, 139(3). 2013.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{ibraguimova2013,\n\ttitle = {Investigation of oxygen dissociation and vibrational relaxation at temperatures 4000--10 800 {K}},\n\tvolume = {139},\n\tdoi = {10.1063/1.4813070},\n\tnumber = {3},\n\tjournal = {The Journal of Chemical Physics},\n\tauthor = {Ibraguimova, L B and Sergievskaya, A L and Levashov, V Yu. and Shatalov, O P and Tunik, Yu. V and Zabelinskii, I E},\n\tyear = {2013},\n}\n\n\n\n
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\n \n\n \n \n Morgenstern, J.\n\n\n \n \n \n \n Full Configuration Low Boom Model and Grids for 2014 Sonic Boom Prediction Workshop.\n \n \n \n\n\n \n\n\n\n In January 2013. AIAA Paper 2013-0647\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{morgenstern2013,\n\ttitle = {Full {Configuration} {Low} {Boom} {Model} and {Grids} for 2014 {Sonic} {Boom} {Prediction} {Workshop}},\n\tisbn = {978-1-62410-181-6},\n\tdoi = {10.2514/6.2013-647},\n\tlanguage = {en},\n\turldate = {2023-01-11},\n\tpublisher = {AIAA Paper 2013-0647},\n\tauthor = {Morgenstern, John},\n\tmonth = jan,\n\tyear = {2013},\n}\n\n\n\n
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\n \n\n \n \n Bultel, A.; and Annaloro, J.\n\n\n \n \n \n \n \n Elaboration of collisional–radiative models for flows related to planetary entries into the Earth and Mars atmospheres.\n \n \n \n \n\n\n \n\n\n\n Plasma Sources Science and Technology, 22(2). March 2013.\n Publisher: IOP Publishing\n\n\n\n
\n\n\n\n \n \n \"ElaborationPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{bultel2013,\n\ttitle = {Elaboration of collisional–radiative models for flows related to planetary entries into the {Earth} and {Mars} atmospheres},\n\tvolume = {22},\n\turl = {https://iopscience.iop.org/article/10.1088/0963-0252/22/2/025008},\n\tdoi = {10.1088/0963-0252/22/2/025008},\n\tabstract = {The most relevant way to predict the excited state number density in a nonequilibrium plasma is to elaborate a collisional-radiative (CR) model taking into account most of the collisional and radiative elementary processes. Three examples of such an elaboration are given in this paper in the case of various plasma flows related to planetary atmospheric entries. The case of theoretical determination of nitrogen atom ionization or recombination global rate coefficients under electron impact is addressed first. The global rate coefficient can be implemented in multidimensional computational fluid dynamics calculations. The case of relaxation after a shock front crossing a gas of N2 molecules treated in the framework of the Rankine-Hugoniot assumptions is also studied. The vibrational and electronic specific CR model elaborated in this case allows one to understand how the plasma reaches equilibrium and to estimate the role of the radiative losses. These radiative losses play a significant role at low pressure in the third case studied. This case concerns CO2 plasma jets inductively generated in high enthalpy wind tunnels used as ground test facilities. We focus our attention on the behaviour of CO and C2 electronic excited states, the radiative signature of which can be particularly significant in this type of plasma. These three cases illustrate the elaboration of CR models and their coupling with balance equations. © 2013 IOP Publishing Ltd.},\n\tnumber = {2},\n\tjournal = {Plasma Sources Science and Technology},\n\tauthor = {Bultel, Arnaud and Annaloro, Julien},\n\tmonth = mar,\n\tyear = {2013},\n\tnote = {Publisher: IOP Publishing},\n}\n\n\n\n
\n
\n\n\n
\n The most relevant way to predict the excited state number density in a nonequilibrium plasma is to elaborate a collisional-radiative (CR) model taking into account most of the collisional and radiative elementary processes. Three examples of such an elaboration are given in this paper in the case of various plasma flows related to planetary atmospheric entries. The case of theoretical determination of nitrogen atom ionization or recombination global rate coefficients under electron impact is addressed first. The global rate coefficient can be implemented in multidimensional computational fluid dynamics calculations. The case of relaxation after a shock front crossing a gas of N2 molecules treated in the framework of the Rankine-Hugoniot assumptions is also studied. The vibrational and electronic specific CR model elaborated in this case allows one to understand how the plasma reaches equilibrium and to estimate the role of the radiative losses. These radiative losses play a significant role at low pressure in the third case studied. This case concerns CO2 plasma jets inductively generated in high enthalpy wind tunnels used as ground test facilities. We focus our attention on the behaviour of CO and C2 electronic excited states, the radiative signature of which can be particularly significant in this type of plasma. These three cases illustrate the elaboration of CR models and their coupling with balance equations. © 2013 IOP Publishing Ltd.\n
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\n \n\n \n \n Chettle, A. J; Erdem, E.; and Kontis, K.\n\n\n \n \n \n \n Edney IV Interaction Studies at Mach 5.\n \n \n \n\n\n \n\n\n\n In Bonazza, R.; and Ranjan, D., editor(s), 2013. \n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{chettle2013,\n\ttitle = {Edney {IV} {Interaction} {Studies} at {Mach} 5},\n\tauthor = {Chettle, Alan J and Erdem, Erinc and Kontis, Konstantinos},\n\teditor = {Bonazza, Riccardo and Ranjan, Devesh},\n\tyear = {2013},\n}\n\n\n\n
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\n \n\n \n \n Alkandry, H.; Boyd, I. D; and Martin, A.\n\n\n \n \n \n \n Comparison of Models for Mixture Transport Properties for Numerical Simulations of Ablative Heat-Shields.\n \n \n \n\n\n \n\n\n\n In Grapevine, TX, January 2013. \\AIAA Paper\\ 2013-0303\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{alkandry2013,\n\taddress = {Grapevine, TX},\n\ttitle = {Comparison of {Models} for {Mixture} {Transport} {Properties} for {Numerical} {Simulations} of {Ablative} {Heat}-{Shields}},\n\tdoi = {10.2514/6.2013-303},\n\tpublisher = {\\{AIAA Paper\\} 2013-0303},\n\tauthor = {Alkandry, Hicham and Boyd, Iain D and Martin, Alexandre},\n\tmonth = jan,\n\tyear = {2013},\n}\n\n\n\n
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\n \n\n \n \n Duffa, G.\n\n\n \n \n \n \n Ablative Thermal Protection Systems Modeling.\n \n \n \n\n\n \n\n\n\n American Institute of Aeronautics and Astronautics, Inc., May 2013.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@book{duffa2013,\n\ttitle = {Ablative {Thermal} {Protection} {Systems} {Modeling}},\n\tpublisher = {American Institute of Aeronautics and Astronautics, Inc.},\n\tauthor = {Duffa, Georges},\n\tmonth = may,\n\tyear = {2013},\n\tdoi = {10.2514/4.101717},\n}\n\n\n\n
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\n \n\n \n \n Eason, T. G; Spottswood, S M.; Chona, R.; and Penmetsa, R.\n\n\n \n \n \n \n \n A Structures Perspective on the Challenges Associated with Analyzing a Reusable Hypersonic Platform.\n \n \n \n \n\n\n \n\n\n\n In 2013. \n \n\n\n\n
\n\n\n\n \n \n \"APaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{eason2013,\n\ttitle = {A {Structures} {Perspective} on the {Challenges} {Associated} with {Analyzing} a {Reusable} {Hypersonic} {Platform}},\n\turl = {http://arc.aiaa.org},\n\tdoi = {10.2514/6.2013-1747},\n\tabstract = {The AFRL Structural Sciences Center (SSC) is researching and developing methods for structural-scale simulation to address those deficiencies in the analysis of extreme-environment structures that have historically stymied the USAF and the aerospace community at large. To address these challenges, the Structural Sciences Center at the Air Force Research Laboratory, has embarked on a campaign with industry to uncover the knowledge gaps associated with defining the structural margins for a reusable Mach 5-7 air breathing class hypersonic vehicle. The current focus of this campaign includes: (1) reviewing the structural challenges encountered in past high-speed structures programs, (2) assessing the current state-of-the-art in design and analysis methods; and (3) identifying critical knowledge gaps in current methods. Each of these areas will be discussed and presented, with the goal of energizing the aerospace community to participate in helping to define and develop an appropriate series of relevant benchmark challenge problems to address key critical knowledge gaps.},\n\tauthor = {Eason, Thomas G and Spottswood, S Michael and Chona, Ravi and Penmetsa, Ravi},\n\tyear = {2013},\n}\n\n\n\n
\n
\n\n\n
\n The AFRL Structural Sciences Center (SSC) is researching and developing methods for structural-scale simulation to address those deficiencies in the analysis of extreme-environment structures that have historically stymied the USAF and the aerospace community at large. To address these challenges, the Structural Sciences Center at the Air Force Research Laboratory, has embarked on a campaign with industry to uncover the knowledge gaps associated with defining the structural margins for a reusable Mach 5-7 air breathing class hypersonic vehicle. The current focus of this campaign includes: (1) reviewing the structural challenges encountered in past high-speed structures programs, (2) assessing the current state-of-the-art in design and analysis methods; and (3) identifying critical knowledge gaps in current methods. Each of these areas will be discussed and presented, with the goal of energizing the aerospace community to participate in helping to define and develop an appropriate series of relevant benchmark challenge problems to address key critical knowledge gaps.\n
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\n  \n 2012\n \n \n (25)\n \n \n
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\n \n\n \n \n Wang, M.; Mani, A.; and Gordeyev, S.\n\n\n \n \n \n \n Physics and Computation of Aero-Optics.\n \n \n \n\n\n \n\n\n\n Annual Review of Fluid Mechanics, 44: 299–321. 2012.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{wang2012,\n\ttitle = {Physics and {Computation} of {Aero}-{Optics}},\n\tvolume = {44},\n\tdoi = {10.1146/annurev-fluid-120710-101152},\n\tjournal = {Annual Review of Fluid Mechanics},\n\tauthor = {Wang, Meng and Mani, Ali and Gordeyev, Stanislav},\n\tyear = {2012},\n\tpages = {299--321},\n}\n\n\n\n
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\n \n\n \n \n Hosder, S.; and Bettis, B. R.\n\n\n \n \n \n \n Uncertainty and Sensitivity Analysis for Reentry Flows with Inherent and Model-Form Uncertainties.\n \n \n \n\n\n \n\n\n\n Journal of Spacecraft and Rockets, 49(2): 193–206. March 2012.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{hosder2012,\n\ttitle = {Uncertainty and {Sensitivity} {Analysis} for {Reentry} {Flows} with {Inherent} and {Model}-{Form} {Uncertainties}},\n\tvolume = {49},\n\tissn = {0022-4650, 1533-6794},\n\tdoi = {10.2514/1.A32102},\n\tlanguage = {en},\n\tnumber = {2},\n\turldate = {2024-04-01},\n\tjournal = {Journal of Spacecraft and Rockets},\n\tauthor = {Hosder, Serhat and Bettis, Benjamin R.},\n\tmonth = mar,\n\tyear = {2012},\n\tpages = {193--206},\n}\n\n\n\n\n\n\n\n
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\n \n\n \n \n George S.;Dennis, Brian H.;Baker; Daniel P.;Kennon, S. R.; and Helcio R.B.;Colaco, M. J. D.\n\n\n \n \n \n \n Inverse Problems in Aerodynamics, Heat Transfer, Elasticity and Materials Design.\n \n \n \n\n\n \n\n\n\n International Journal of Aeronautical and Space Sciences, 13(4): 405–420. 2012.\n Publisher: The Korean Society for Aeronautical and Space Sciences\n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{dulikravich2012,\n\ttitle = {Inverse {Problems} in {Aerodynamics}, {Heat} {Transfer}, {Elasticity} and {Materials} {Design}},\n\tvolume = {13},\n\tdoi = {10.5139/IJASS.2012.13.4.405},\n\tnumber = {4},\n\tjournal = {International Journal of Aeronautical and Space Sciences},\n\tauthor = {{George S.;Dennis, Brian H.;Baker, Daniel P.;Kennon, Stephen R.;Orlande, Helcio R.B.;Colaco, Marcelo J.; Dulikravich}},\n\tyear = {2012},\n\tnote = {Publisher: The Korean Society for Aeronautical and Space Sciences},\n\tkeywords = {aerodynamic design, inverse problems, material design, thermoelasticity},\n\tpages = {405--420},\n}\n\n\n\n
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\n \n\n \n \n PATEL, M.; SAURABH, K.; PRASAD, V. V. B.; and SUBRAHMANYAM, J.\n\n\n \n \n \n \n High temperature C/C–SiC composite by liquid silicon infiltration: a literature review.\n \n \n \n\n\n \n\n\n\n Bulletin of Materials Science, 35(1): 63–73. February 2012.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{patel_high_2012,\n\ttitle = {High temperature {C}/{C}–{SiC} composite by liquid silicon infiltration: a literature review},\n\tvolume = {35},\n\tissn = {0973-7669},\n\tdoi = {10.1007/s12034-011-0247-5},\n\tabstract = {The ceramic matrix carbon fibre (CMC) reinforced composite has received great attention for use in aerospace engineering. In aerospace, the atmosphere is highly oxidative and experiences very high temperature. In addition to this, the materials require high thermal stability and high abrasion resistance in that atmosphere. The C/C–SiC composite meets with these requirements. In this paper, the C/C–SiC composite by liquid silicon infiltration is reviewed thoroughly.},\n\tnumber = {1},\n\tjournal = {Bulletin of Materials Science},\n\tauthor = {PATEL, MANISH and SAURABH, KUMAR and PRASAD, V. V. BHANU and SUBRAHMANYAM, J.},\n\tmonth = feb,\n\tyear = {2012},\n\tpages = {63--73},\n}\n\n\n\n
\n
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\n The ceramic matrix carbon fibre (CMC) reinforced composite has received great attention for use in aerospace engineering. In aerospace, the atmosphere is highly oxidative and experiences very high temperature. In addition to this, the materials require high thermal stability and high abrasion resistance in that atmosphere. The C/C–SiC composite meets with these requirements. In this paper, the C/C–SiC composite by liquid silicon infiltration is reviewed thoroughly.\n
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\n \n\n \n \n Kawai, S.; and Larsson, J.\n\n\n \n \n \n \n Wall-modeling in large eddy simulation: Length scales, grid resolution, and accuracy.\n \n \n \n\n\n \n\n\n\n Physics of Fluids, 24(1): 015105. January 2012.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{kawai2012,\n\ttitle = {Wall-modeling in large eddy simulation: {Length} scales, grid resolution, and accuracy},\n\tvolume = {24},\n\tissn = {1070-6631, 1089-7666},\n\tshorttitle = {Wall-modeling in large eddy simulation},\n\tdoi = {10.1063/1.3678331},\n\tlanguage = {en},\n\tnumber = {1},\n\turldate = {2023-01-11},\n\tjournal = {Physics of Fluids},\n\tauthor = {Kawai, Soshi and Larsson, Johan},\n\tmonth = jan,\n\tyear = {2012},\n\tpages = {015105},\n}\n\n\n\n
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\n \n\n \n \n Ren, W.; and Liu, H.\n\n\n \n \n \n \n Study on the Effect of Compressibility and Knudsen Number on Aero Optics in Supersonic/Hypersonic Flows.\n \n \n \n\n\n \n\n\n\n In New Orleans, Louisiana, June 2012. AIAA 2012-2988\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{ren2012,\n\taddress = {New Orleans, Louisiana},\n\ttitle = {Study on the {Effect} of {Compressibility} and {Knudsen} {Number} on {Aero} {Optics} in {Supersonic}/{Hypersonic} {Flows}},\n\tpublisher = {AIAA 2012-2988},\n\tauthor = {Ren, Wei and Liu, Hong},\n\tmonth = jun,\n\tyear = {2012},\n}\n\n\n\n
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\n \n\n \n \n Fidkowski, K. J.; and Darmofal, D. L.\n\n\n \n \n \n \n \n Review of Output-Based Error Estimation and Mesh Adaptation in Computational Fluid Dynamics.\n \n \n \n \n\n\n \n\n\n\n AIAA Journal, 49(4): 673–694. April 2012.\n \n\n\n\n
\n\n\n\n \n \n \"ReviewPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{fidkowski2012,\n\ttitle = {Review of {Output}-{Based} {Error} {Estimation} and {Mesh} {Adaptation} in {Computational} {Fluid} {Dynamics}},\n\tvolume = {49},\n\turl = {https://arc.aiaa.org/doi/abs/10.2514/1.J050073},\n\tdoi = {10.2514/1.J050073},\n\tabstract = {Error estimation and control are critical ingredients for improving the reliability of computational simulations. Adjoint-based techniques can be used to both estimate the error in chosen solution outputs and to provide local indicators for adaptive refinement. This article reviews recent work on these techniques for computational fluid dynamics applications in aerospace engineering. The definition of the adjoint as the sensitivity of an output to residual source perturbations is used to derive both the adjoint equation, in fully discrete and variational formulations, and the adjoint-weighted residual method for error estimation. Assumptions and approximations made in the calculations are discussed. Presentation of the discrete and variational formulations enables a side-by-side comparison of recent work in output-error estimation using the finite volume method and the finite element method. Techniques for adapting meshes using output-error indicators are also reviewed. Recent adaptive results from a variety of laminar and Reynolds-averaged Navier-Stokes applications show the power of output-based adaptivemethods for improving the robustness of computational fluid dynamics computations. However, challenges and areas of additional future research remain, including computable error bounds and robust mesh adaptation mechanics. Copyright © 2011 by Krzysztof J. Fidkowski and David L. Darmofal. Published by the American Institute of Aeronautics and Astronautics, Inc.},\n\tnumber = {4},\n\tjournal = {AIAA Journal},\n\tauthor = {Fidkowski, Krzysztof J. and Darmofal, David L.},\n\tmonth = apr,\n\tyear = {2012},\n\tkeywords = {Aerodynamic Flows, Aerodynamic Simulation, Aerospace Designs, CFD Simulation, Discontinuous Galerkin Method, Finite Volume Method, Galerkin Finite Element Method, Mesh Generation, Reynolds Averaged Navier Stokes, Sonic Booms},\n\tpages = {673--694},\n}\n\n\n\n
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\n Error estimation and control are critical ingredients for improving the reliability of computational simulations. Adjoint-based techniques can be used to both estimate the error in chosen solution outputs and to provide local indicators for adaptive refinement. This article reviews recent work on these techniques for computational fluid dynamics applications in aerospace engineering. The definition of the adjoint as the sensitivity of an output to residual source perturbations is used to derive both the adjoint equation, in fully discrete and variational formulations, and the adjoint-weighted residual method for error estimation. Assumptions and approximations made in the calculations are discussed. Presentation of the discrete and variational formulations enables a side-by-side comparison of recent work in output-error estimation using the finite volume method and the finite element method. Techniques for adapting meshes using output-error indicators are also reviewed. Recent adaptive results from a variety of laminar and Reynolds-averaged Navier-Stokes applications show the power of output-based adaptivemethods for improving the robustness of computational fluid dynamics computations. However, challenges and areas of additional future research remain, including computable error bounds and robust mesh adaptation mechanics. Copyright © 2011 by Krzysztof J. Fidkowski and David L. Darmofal. Published by the American Institute of Aeronautics and Astronautics, Inc.\n
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\n \n\n \n \n Panesi, M.; Jaffe, R. L; Schwenke, D. W; and Magin, T. E\n\n\n \n \n \n \n Rovibrational internal energy transfer and dissociation of N\\textsubscript\\2\\(\\textsuperscript\\1\\$Σ$+g)-N(\\textsuperscript\\4\\S\\textsubscript\\u\\) system in hypersonic flows.\n \n \n \n\n\n \n\n\n\n The Journal of Chemical Physics, 138(4): 1–16. 2012.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{panesi2012a,\n\ttitle = {Rovibrational internal energy transfer and dissociation of {N}{\\textbackslash}textsubscript\\{2\\}({\\textbackslash}textsuperscript\\{1\\}\\$Σ\\$+g)-{N}({\\textbackslash}textsuperscript\\{4\\}{S}{\\textbackslash}textsubscript\\{u\\}) system in hypersonic flows},\n\tvolume = {138},\n\tnumber = {4},\n\tjournal = {The Journal of Chemical Physics},\n\tauthor = {Panesi, Marco and Jaffe, Richard L and Schwenke, David W and Magin, Thierry E},\n\tyear = {2012},\n\tpages = {1--16},\n}\n\n\n\n
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\n \n\n \n \n Visbal, M. R.\n\n\n \n \n \n \n \n Onset of vortex breakdown above a pitching delta wing.\n \n \n \n \n\n\n \n\n\n\n AIAA Journal, 32(8): 1568–1575. May 2012.\n \n\n\n\n
\n\n\n\n \n \n \"OnsetPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{visbal2012,\n\ttitle = {Onset of vortex breakdown above a pitching delta wing},\n\tvolume = {32},\n\turl = {https://arc.aiaa.org/doi/abs/10.2514/3.12145},\n\tdoi = {10.2514/3.12145},\n\tabstract = {Computational results are presented for transient vortex breakdown above a delta wing subject to a pitch-andhold maneuver to high angle of attack. The flows are simulated by solving the full three-dimensional Navier- Stokes equations on a moving grid using the implicit Beam-Warming algorithm. An assessment of the effects of numerical resolution and favorable comparison with experimental data suggest the computational approach captures the basic dynamics of the onset and initial stages of transient breakdown. The pressure gradient along the vortex axis is found to play a dominant role in the initiation of breakdown. A description of the three-dimensional instantaneous structure of the flowfield is provided for the first time using critical-point theory. The reversed-flow region in the vortex core is associated with pairs of opposite spiral/saddle critical points. At its onset, the vortex breakdown is fairly axisymmetric; however, as it proceeds upstream and a stronger jump takes place along the axis, asymmetric effects become important and culminate in the formation of a bubble-type breakdown. This bubble structure is open and contains within itself a pair of stagnation points that are diametrically opposed and that rotate in the same sense as the upstream swirling flow. These critical points suggest the existence of azimuthal disturbances in the breakdown region. The bubble sectional topology is also found in agreement with recent experimental measurements. © 1994 American Institute of Aeronautics and Astronautics, Inc., All rights reserved.},\n\tnumber = {8},\n\tjournal = {AIAA Journal},\n\tauthor = {Visbal, Miguel R.},\n\tmonth = may,\n\tyear = {2012},\n\tkeywords = {Angle of Attack, Cambered Delta Wing, Flow Visualization Techniques, Freestream Mach Number, Navier Stokes Equations, Shear Layers, Streamlines Pattern, Taylor Vortex Flow, Velocity Profiles, Vortex Breakdown},\n\tpages = {1568--1575},\n}\n\n\n\n
\n
\n\n\n
\n Computational results are presented for transient vortex breakdown above a delta wing subject to a pitch-andhold maneuver to high angle of attack. The flows are simulated by solving the full three-dimensional Navier- Stokes equations on a moving grid using the implicit Beam-Warming algorithm. An assessment of the effects of numerical resolution and favorable comparison with experimental data suggest the computational approach captures the basic dynamics of the onset and initial stages of transient breakdown. The pressure gradient along the vortex axis is found to play a dominant role in the initiation of breakdown. A description of the three-dimensional instantaneous structure of the flowfield is provided for the first time using critical-point theory. The reversed-flow region in the vortex core is associated with pairs of opposite spiral/saddle critical points. At its onset, the vortex breakdown is fairly axisymmetric; however, as it proceeds upstream and a stronger jump takes place along the axis, asymmetric effects become important and culminate in the formation of a bubble-type breakdown. This bubble structure is open and contains within itself a pair of stagnation points that are diametrically opposed and that rotate in the same sense as the upstream swirling flow. These critical points suggest the existence of azimuthal disturbances in the breakdown region. The bubble sectional topology is also found in agreement with recent experimental measurements. © 1994 American Institute of Aeronautics and Astronautics, Inc., All rights reserved.\n
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\n \n\n \n \n Nicholson, D. W.\n\n\n \n \n \n \n On finite element analysis of an inverse problem in elasticity.\n \n \n \n\n\n \n\n\n\n Inverse Problems in Science and Engineering, 20(5): 735–748. September 2012.\n Publisher: Taylor & Francis\n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{nicholson2012,\n\ttitle = {On finite element analysis of an inverse problem in elasticity},\n\tvolume = {20},\n\tdoi = {10.1080/17415977.2012.668677},\n\tabstract = {This investigation concerns an inverse problem modelled by the finite element method. For a given mesh and set of physical properties, even though a well-posed direct problem possesses a unique sol...},\n\tnumber = {5},\n\tjournal = {Inverse Problems in Science and Engineering},\n\tauthor = {Nicholson, David W.},\n\tmonth = sep,\n\tyear = {2012},\n\tnote = {Publisher: Taylor \\& Francis},\n\tkeywords = {finite element modelling, inverse modelling, matrix nonsingularity condition, mesh modification},\n\tpages = {735--748},\n}\n\n\n\n
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\n This investigation concerns an inverse problem modelled by the finite element method. For a given mesh and set of physical properties, even though a well-posed direct problem possesses a unique sol...\n
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\n \n\n \n \n Bisek, N. J.; Boyd, I. D.; and Poggie, J.\n\n\n \n \n \n \n Numerical Study of Plasma-Assisted Aerodynamic Control for Hypersonic Vehicles.\n \n \n \n\n\n \n\n\n\n Journal of Spacecraft and Rockets, 46(3): 568–576. May 2012.\n Publisher: American Institute of Aeronautics and Astronautics Inc.\n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{bisek2012,\n\ttitle = {Numerical {Study} of {Plasma}-{Assisted} {Aerodynamic} {Control} for {Hypersonic} {Vehicles}},\n\tvolume = {46},\n\tdoi = {10.2514/1.39032},\n\tabstract = {Plasma actuators and various forms of volumetric energy deposition have received a good deal of research attention recently as a means of hypersonic flight control. An open question remains as to whether the required power expenditures for such devices can be achieved for practical systems. To address this issue, a numerical study is carried out for hypersonic flow over a blunt-nose elliptic cone to determine the amount of energy deposition necessary for flight control. Energy deposition is simulated by means of a phenomenological dissipative heating model. A parametric study of the effects of energy deposition is carried outfor several blunt elliptic cone configurations. Three different volumetric energy deposition patterns are considered: a spherical pattern, a "pancake" pattern (oblate spheroid), and a "bean" pattern (prolate spheroid). The effectiveness of volumetric energy deposition for flight control appears to scale strongly with a nondimensional parameter based on the freestream flow kinetic energy flux. Copyright Clearance Center Inc.,.},\n\tnumber = {3},\n\tjournal = {Journal of Spacecraft and Rockets},\n\tauthor = {Bisek, Nicholas J. and Boyd, Iain D. and Poggie, Jonathan},\n\tmonth = may,\n\tyear = {2012},\n\tnote = {Publisher: American Institute of Aeronautics and Astronautics Inc.},\n\tkeywords = {Bow Shock, Flight Control, Freestream Conditions, Hypersonic Flows, Hypersonic Vehicles, Pressure Coefficient, Thermal Nonequilibrium, Thermal Protection System, Vibrational Energy, Wall Temperature},\n\tpages = {568--576},\n}\n\n\n\n
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\n Plasma actuators and various forms of volumetric energy deposition have received a good deal of research attention recently as a means of hypersonic flight control. An open question remains as to whether the required power expenditures for such devices can be achieved for practical systems. To address this issue, a numerical study is carried out for hypersonic flow over a blunt-nose elliptic cone to determine the amount of energy deposition necessary for flight control. Energy deposition is simulated by means of a phenomenological dissipative heating model. A parametric study of the effects of energy deposition is carried outfor several blunt elliptic cone configurations. Three different volumetric energy deposition patterns are considered: a spherical pattern, a \"pancake\" pattern (oblate spheroid), and a \"bean\" pattern (prolate spheroid). The effectiveness of volumetric energy deposition for flight control appears to scale strongly with a nondimensional parameter based on the freestream flow kinetic energy flux. Copyright Clearance Center Inc.,.\n
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\n \n\n \n \n Hou, G.; Wang, J.; and Layton, A.\n\n\n \n \n \n \n \n Numerical Methods for Fluid-Structure Interaction — A Review.\n \n \n \n \n\n\n \n\n\n\n Communications in Computational Physics, 12(2): 337–377. August 2012.\n Publisher: Cambridge University Press\n\n\n\n
\n\n\n\n \n \n \"NumericalPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{hou2012,\n\ttitle = {Numerical {Methods} for {Fluid}-{Structure} {Interaction} — {A} {Review}},\n\tvolume = {12},\n\turl = {https://www.cambridge.org/core/journals/communications-in-computational-physics/article/numerical-methods-for-fluidstructure-interaction-a-review/359AE654882EAFB08CAAA862AC7B05AC},\n\tdoi = {10.4208/CICP.291210.290411S},\n\tabstract = {The interactions between incompressible fluid flows and immersed structures are nonlinear multi-physics phenomena that have applications to a wide range of scientific and engineering disciplines. In this article, we review representative numerical methods based on conforming and non-conforming meshes that are currently available for computing fluid-structure interaction problems, with an emphasis on some of the recent developments in the field. A goal is to categorize the selected methods and assess their accuracy and efficiency. We discuss challenges faced by researchers in this field, and we emphasize the importance of interdisciplinary effort for advancing the study in fluid-structure interactions.},\n\tnumber = {2},\n\tjournal = {Communications in Computational Physics},\n\tauthor = {Hou, Gene and Wang, Jin and Layton, Anita},\n\tmonth = aug,\n\tyear = {2012},\n\tnote = {Publisher: Cambridge University Press},\n\tkeywords = {65-02, 65Z05, 74F10, Fluid-structure interaction, conforming and non-conforming meshes, immersed methods},\n\tpages = {337--377},\n}\n\n\n\n
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\n The interactions between incompressible fluid flows and immersed structures are nonlinear multi-physics phenomena that have applications to a wide range of scientific and engineering disciplines. In this article, we review representative numerical methods based on conforming and non-conforming meshes that are currently available for computing fluid-structure interaction problems, with an emphasis on some of the recent developments in the field. A goal is to categorize the selected methods and assess their accuracy and efficiency. We discuss challenges faced by researchers in this field, and we emphasize the importance of interdisciplinary effort for advancing the study in fluid-structure interactions.\n
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\n \n\n \n \n Allmaras, S. R; Johnson, F. T; and Spalart, P. R\n\n\n \n \n \n \n Modications and Clarications for the Implementation of the Spalart-Allmaras Turbulence Model.\n \n \n \n\n\n \n\n\n\n In pages 9–13, 2012. Seventh International Conference on Computational Fluid Dynamics\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n\n\n\n
\n 
@inproceedings{allmaras2012,\n\ttitle = {Modications and {Clarications} for the {Implementation} of the {Spalart}-{Allmaras} {Turbulence} {Model}},\n\tabstract = {We present modications to the Spalart-Allmaras (S-A) turbulence model targeted toward situations of under-resolved grids and unphysical transient states. These modications are formulated to be passive to the original model in well resolved owelds and should produce negligible dierences in most cases. They are motivated primarily by numerical issues near the interface between turbulent and irrotational regions. We also comment on the appropriate form of S-A for compressible ows, the inclusion of the laminar suppression term for fully turbulent ows, and the use of maximum value limiters on the turbulence solution. We also present a new analytic solution to S-A for law of the wall velocity.},\n\tpublisher = {Seventh International Conference on Computational Fluid Dynamics},\n\tauthor = {Allmaras, Steven R and Johnson, Forrester T and Spalart, Philippe R},\n\tyear = {2012},\n\tkeywords = {Computational Fluid Dynamics, Turbulence Modeling},\n\tpages = {9--13},\n}\n\n\n\n
\n
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\n We present modications to the Spalart-Allmaras (S-A) turbulence model targeted toward situations of under-resolved grids and unphysical transient states. These modications are formulated to be passive to the original model in well resolved owelds and should produce negligible dierences in most cases. They are motivated primarily by numerical issues near the interface between turbulent and irrotational regions. We also comment on the appropriate form of S-A for compressible ows, the inclusion of the laminar suppression term for fully turbulent ows, and the use of maximum value limiters on the turbulence solution. We also present a new analytic solution to S-A for law of the wall velocity.\n
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\n \n\n \n \n Alonso, J. J.; and Colonno, M. R.\n\n\n \n \n \n \n \n Multidisciplinary Optimization with Applications to Sonic-Boom Minimization.\n \n \n \n \n\n\n \n\n\n\n Annual Review of Fluid Mechanics, 44(1): 505–526. January 2012.\n Publisher: Annual Reviews\n\n\n\n
\n\n\n\n \n \n \"MultidisciplinaryPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{alonso2012,\n\ttitle = {Multidisciplinary {Optimization} with {Applications} to {Sonic}-{Boom} {Minimization}},\n\tvolume = {44},\n\turl = {http://www.annualreviews.org/doi/10.1146/annurev-fluid-120710-101133},\n\tdoi = {10.1146/annurev-fluid-120710-101133},\n\tabstract = {This article presents a review of key historical contributions, the current status, and future research avenues in support of the development of supersonic aircraft that are sufficiently quiet so that they can be allowed to fly supersonically over land. For this goal to be achievable, in addition to overcoming many other challenges in aerodynamics, structures, propulsion, acoustics, and aeroservoelasticity, the pressure signature created by the aircraft must be such that, when it reaches the ground, (a) it can barely be perceived by the human ear, and (b) it results in disturbances to man-made structures that do not exceed the threshold of annoyance for a significant percentage of the population. In other words, the ground-boom signature must meet a number of key constraints that can be appropriately quantified. In designing aircraft with low sonic booms, it is important to understand (a) how pressure disturbances are generated and how they propagate through the atmosphere, (b) under which conditions will the pressure signature created by an aircraft evolve to generate an acceptable low-boom signature at the ground, and (c) what multidisciplinary trade-offs need to be made to realize low-boom aircraft that are also economically and environmentally compliant. This article discusses each of these areas separately, assesses the accomplishments in each topic, identifies significant shortcomings, and suggests future research efforts (some already ongoing) that have the potential to yield solutions to all these issues.},\n\tnumber = {1},\n\tjournal = {Annual Review of Fluid Mechanics},\n\tauthor = {Alonso, Juan J. and Colonno, Michael R.},\n\tmonth = jan,\n\tyear = {2012},\n\tnote = {Publisher: Annual Reviews},\n\tkeywords = {Aircraft design, Boom propagation, Noise, Perceived loudness, Robust design, Supersonic design, Supersonic flow},\n\tpages = {505--526},\n}\n\n\n\n
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\n This article presents a review of key historical contributions, the current status, and future research avenues in support of the development of supersonic aircraft that are sufficiently quiet so that they can be allowed to fly supersonically over land. For this goal to be achievable, in addition to overcoming many other challenges in aerodynamics, structures, propulsion, acoustics, and aeroservoelasticity, the pressure signature created by the aircraft must be such that, when it reaches the ground, (a) it can barely be perceived by the human ear, and (b) it results in disturbances to man-made structures that do not exceed the threshold of annoyance for a significant percentage of the population. In other words, the ground-boom signature must meet a number of key constraints that can be appropriately quantified. In designing aircraft with low sonic booms, it is important to understand (a) how pressure disturbances are generated and how they propagate through the atmosphere, (b) under which conditions will the pressure signature created by an aircraft evolve to generate an acceptable low-boom signature at the ground, and (c) what multidisciplinary trade-offs need to be made to realize low-boom aircraft that are also economically and environmentally compliant. This article discusses each of these areas separately, assesses the accomplishments in each topic, identifies significant shortcomings, and suggests future research efforts (some already ongoing) that have the potential to yield solutions to all these issues.\n
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\n \n\n \n \n Kim, M.; Gülhan, A.; and Boyd, I. D\n\n\n \n \n \n \n Modeling of Electron Energy Phenomena in Hypersonic Flows.\n \n \n \n\n\n \n\n\n\n Journal of Thermophysics and Heat Transfer, 26(2). 2012.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{kim2012,\n\ttitle = {Modeling of {Electron} {Energy} {Phenomena} in {Hypersonic} {Flows}},\n\tvolume = {26},\n\tissn = {08878722/12},\n\tdoi = {10.2514/1.T3716},\n\tabstract = {Studies are described for modeling electron energy phenomena for hypersonic flows. The electron energy must be modeled separately from other energy modes because it may have a significant effect on vibrational relaxation and chemical reactions. Whenever flows are in a strong thermal nonequilibrium state, an electron energy equation should be considered. In the considered electron energy equation, the electron energy relaxations of each energy mode are accounted for, which include translational-electron, rotational-electron, and vibrational-electron energy relaxation. To avoid a singularity of the Jacobian in the electron energy equation, we introduce a modified electron energy expression. The suggested electron-energy model is implemented into a hypersonic flow code for both explicit and implicit methods. In the present study, we numerically simulate the electron energy with electron-vibrational relaxation for diatomic nitrogen. For the assessment of the electron-energy model, we simulate several cases, which are a plasma wind-tunnel, a radio attenuation measurement (RAM)-C case, the entry of the automated transfer vehicle, and the Stardust reentry capsule. Nomenclature b 0 = scattering parameter for 90 deg, Ze 2 †=12" 0 kT e †, m 2 C V;e = electron specific heat capacity, 3=2† R=M e †, J=kg K† c s = species charge D s = species diffusion coefficients, m 2 =s E e = electron energy, e ‰C v;e T e ‡ 1=2†u 2 ‡ v 2 ‡ w 2 †Š E i;f = first ionization energy per unit mass, J=kg E rot = rotational energy E vib = vibrational energy e = elementary charge, 1:6022 10 19 C e e = electron energy per unit mass of electrons, C V;e T e ‡ 1=2†u 2 ‡ v 2 ‡ w 2 † e e = modified electron energy per unit mass, e =†e e e vib;s = vibrational energy per unit mass F = inviscid flux vector H = total enthalpy per unit mass, J=kg J e = electron diffusion flux k = Boltzmann constant, 1:38065 10 23 ‰m 2 kg s 2 K 1 Š k ev 0;j = vibrational-excitation rate coefficient from vibrational state 0 to j, m 3 =s M s = molecular weight of species s m s = species mass, kg n = unit vector normal to computational cell face n e = electron number density, m 3 p e = electron pressure, Pa Q = vector of conserved variables q e = electron heat flux R = universal gas constant, 8314.3, J=kg mole K S chem;e = electron energy gained by the electrons generated from chemical reactions S e = source term S e;modified = modified source term of the electron energy equation that includes the electron pressure term S epg = approximation of the work done on electrons by the electric field induced by the electron pressure gradient S inelastic;e = rate of inelastic energy exchange between electrons and molecules S transe = energy exchange between translational and electron energies T e = electron temperature, K T trans = translational temperature, K T tr = translational-rotational temperature, K T ve = vibrational-electron-electronic temperature, K U = velocity component normal to computational cell face u = flow velocity Y s = species mass fraction v;s = species characteristic vibrational temperature = thermal conductivity, K W=m† D = Debye length, m = viscosity coefficient, N s†=m s = species density, kg=m 3 es = collision cross section for electron and s species, m 2 e = electron viscous stress es = electron-vibrational relaxation time, s \\_ ! e = electron-mass production rate by chemical reactions, kg=m 3 s " 0 = vacuum permittivity, 8:854 10 12 , C V 1 m 1},\n\tnumber = {2},\n\tjournal = {Journal of Thermophysics and Heat Transfer},\n\tauthor = {Kim, Minkwan and Gülhan, Ali and Boyd, Iain D},\n\tyear = {2012},\n}\n\n\n\n
\n
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\n Studies are described for modeling electron energy phenomena for hypersonic flows. The electron energy must be modeled separately from other energy modes because it may have a significant effect on vibrational relaxation and chemical reactions. Whenever flows are in a strong thermal nonequilibrium state, an electron energy equation should be considered. In the considered electron energy equation, the electron energy relaxations of each energy mode are accounted for, which include translational-electron, rotational-electron, and vibrational-electron energy relaxation. To avoid a singularity of the Jacobian in the electron energy equation, we introduce a modified electron energy expression. The suggested electron-energy model is implemented into a hypersonic flow code for both explicit and implicit methods. In the present study, we numerically simulate the electron energy with electron-vibrational relaxation for diatomic nitrogen. For the assessment of the electron-energy model, we simulate several cases, which are a plasma wind-tunnel, a radio attenuation measurement (RAM)-C case, the entry of the automated transfer vehicle, and the Stardust reentry capsule. Nomenclature b 0 = scattering parameter for 90 deg, Ze 2 †=12\" 0 kT e †, m 2 C V;e = electron specific heat capacity, 3=2† R=M e †, J=kg K† c s = species charge D s = species diffusion coefficients, m 2 =s E e = electron energy, e ‰C v;e T e ‡ 1=2†u 2 ‡ v 2 ‡ w 2 †Š E i;f = first ionization energy per unit mass, J=kg E rot = rotational energy E vib = vibrational energy e = elementary charge, 1:6022 10 19 C e e = electron energy per unit mass of electrons, C V;e T e ‡ 1=2†u 2 ‡ v 2 ‡ w 2 † e e = modified electron energy per unit mass, e =†e e e vib;s = vibrational energy per unit mass F = inviscid flux vector H = total enthalpy per unit mass, J=kg J e = electron diffusion flux k = Boltzmann constant, 1:38065 10 23 ‰m 2 kg s 2 K 1 Š k ev 0;j = vibrational-excitation rate coefficient from vibrational state 0 to j, m 3 =s M s = molecular weight of species s m s = species mass, kg n = unit vector normal to computational cell face n e = electron number density, m 3 p e = electron pressure, Pa Q = vector of conserved variables q e = electron heat flux R = universal gas constant, 8314.3, J=kg mole K S chem;e = electron energy gained by the electrons generated from chemical reactions S e = source term S e;modified = modified source term of the electron energy equation that includes the electron pressure term S epg = approximation of the work done on electrons by the electric field induced by the electron pressure gradient S inelastic;e = rate of inelastic energy exchange between electrons and molecules S transe = energy exchange between translational and electron energies T e = electron temperature, K T trans = translational temperature, K T tr = translational-rotational temperature, K T ve = vibrational-electron-electronic temperature, K U = velocity component normal to computational cell face u = flow velocity Y s = species mass fraction v;s = species characteristic vibrational temperature = thermal conductivity, K W=m† D = Debye length, m = viscosity coefficient, N s†=m s = species density, kg=m 3 es = collision cross section for electron and s species, m 2 e = electron viscous stress es = electron-vibrational relaxation time, s _ ! e = electron-mass production rate by chemical reactions, kg=m 3 s \" 0 = vacuum permittivity, 8:854 10 12 , C V 1 m 1\n
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\n \n\n \n \n Townes, C H; and Schawlow, A L\n\n\n \n \n \n \n Microwave Spectroscopy.\n \n \n \n\n\n \n\n\n\n Dover Publications, Inc., 2012.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@book{townes2012,\n\ttitle = {Microwave {Spectroscopy}},\n\tpublisher = {Dover Publications, Inc.},\n\tauthor = {Townes, C H and Schawlow, A L},\n\tyear = {2012},\n}\n\n\n\n
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\n \n\n \n \n Das, R.\n\n\n \n \n \n \n Inverse analysis of Navier–Stokes equations using simplex search method.\n \n \n \n\n\n \n\n\n\n Inverse Problems in Science and Engineering, 20(4): 445–462. June 2012.\n Publisher: Taylor & Francis\n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{das2012a,\n\ttitle = {Inverse analysis of {Navier}–{Stokes} equations using simplex search method},\n\tvolume = {20},\n\tdoi = {10.1080/17415977.2011.629046},\n\tabstract = {The 2-D Navier–Stokes (N–S) equation is solved for the simultaneous estimation of three parameters such as the Reynold's number (Re), the length of the enclosure (lx) and the width of the enclosure...},\n\tnumber = {4},\n\tjournal = {Inverse Problems in Science and Engineering},\n\tauthor = {Das, Ranjan},\n\tmonth = jun,\n\tyear = {2012},\n\tnote = {Publisher: Taylor \\& Francis},\n\tkeywords = {Navier–Stokes equation, Reynold's number, inverse problem, length, parameter estimation, simplex search method, width},\n\tpages = {445--462},\n}\n\n\n\n
\n
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\n The 2-D Navier–Stokes (N–S) equation is solved for the simultaneous estimation of three parameters such as the Reynold's number (Re), the length of the enclosure (lx) and the width of the enclosure...\n
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\n \n\n \n \n Yu, S.; Miller, C. E; Drouin, B. J; and Müller, H. S P\n\n\n \n \n \n \n \n High resolution spectral analysis of oxygen. I. Isotopically invariant Dunham fit for the X3Σg−, a1Δg, b1Σg+ states.\n \n \n \n \n\n\n \n\n\n\n The Journal of Chemical Physics, 137(2): 24304–24304. 2012.\n \n\n\n\n
\n\n\n\n \n \n \"HighPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{yu2012,\n\ttitle = {High resolution spectral analysis of oxygen. {I}. {Isotopically} invariant {Dunham} fit for the {X3Σg}−, {a1Δg}, {b1Σg}+ states},\n\tvolume = {137},\n\turl = {https://doi.org/10.1063/1.4719170},\n\tdoi = {10.1063/1.4719170},\n\tnumber = {2},\n\tjournal = {The Journal of Chemical Physics},\n\tauthor = {Yu, Shanshan and Miller, Charles E and Drouin, Brian J and Müller, Holger S P},\n\tyear = {2012},\n\tpages = {24304--24304},\n}\n\n\n\n
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\n \n\n \n \n Martin, A.; Scalabrin, L. C; and Boyd, I. D\n\n\n \n \n \n \n High performance modeling of atmospheric re-entry vehicles.\n \n \n \n\n\n \n\n\n\n Journal of Physics: Conference Series, 341: 1–12. 2012.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{martin2012,\n\ttitle = {High performance modeling of atmospheric re-entry vehicles},\n\tvolume = {341},\n\tjournal = {Journal of Physics: Conference Series},\n\tauthor = {Martin, Alexandre and Scalabrin, Leonardo C and Boyd, Iain D},\n\tyear = {2012},\n\tpages = {1--12},\n}\n\n\n\n
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\n \n\n \n \n Barbante, P. F.; and Chazot, O.\n\n\n \n \n \n \n \n Flight Extrapolation of Plasma Wind Tunnel Stagnation Region Flowfield.\n \n \n \n \n\n\n \n\n\n\n Journal of Thermophysics and Heat Transfer, 20(3): 493–499. May 2012.\n Publisher: American Institute of Aeronautics and Astronautics Inc.\n\n\n\n
\n\n\n\n \n \n \"FlightPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{barbante2012,\n\ttitle = {Flight {Extrapolation} of {Plasma} {Wind} {Tunnel} {Stagnation} {Region} {Flowfield}},\n\tvolume = {20},\n\turl = {https://arc.aiaa.org/doi/10.2514/1.17185},\n\tdoi = {10.2514/1.17185},\n\tabstract = {Development of reusable space vehicles requires a precise qualification of their thermal protection system materials. The catalytic properties are usually determined in plasma wind tunnels for test conditions relevant to the flight mission program. Therefore, for such a situation, it is important to have a methodology that allows the correct extrapolation of the ground test conditions to the real flight ones and vice-versa. The local heat transfer simulation concept presented in this paper is a possible strategy for accomplishing this task. Computational results show that the ground test conditions are indeed correctly extrapolated to the flight ones and a simple method of accounting for possible discrepancies between the two configurations is presented.},\n\tnumber = {3},\n\tjournal = {Journal of Thermophysics and Heat Transfer},\n\tauthor = {Barbante, P. F. and Chazot, O.},\n\tmonth = may,\n\tyear = {2012},\n\tnote = {Publisher: American Institute of Aeronautics and Astronautics Inc.},\n\tkeywords = {Accurate Computational Fluid Dynamics, Binary Diffusion Coefficient, Boundary Layer Equations, Damköhler Numbers, Freestream Conditions, Heat Transfer, Hypersonic Flows, Shock Layers, Thermal Protection System, Wind Tunnels},\n\tpages = {493--499},\n}\n\n\n\n
\n
\n\n\n
\n Development of reusable space vehicles requires a precise qualification of their thermal protection system materials. The catalytic properties are usually determined in plasma wind tunnels for test conditions relevant to the flight mission program. Therefore, for such a situation, it is important to have a methodology that allows the correct extrapolation of the ground test conditions to the real flight ones and vice-versa. The local heat transfer simulation concept presented in this paper is a possible strategy for accomplishing this task. Computational results show that the ground test conditions are indeed correctly extrapolated to the flight ones and a simple method of accounting for possible discrepancies between the two configurations is presented.\n
\n\n\n
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\n \n\n \n \n Panesi, M.; Magin, T.; Bourdon, A.; Bultel, A.; and Chazot, O.\n\n\n \n \n \n \n \n Fire II Flight Experiment Analysis by Means of a Collisional-Radiative Model.\n \n \n \n \n\n\n \n\n\n\n Journal of Thermophysics and Heat Transfer, 23(2): 236–248. May 2012.\n Publisher: American Institute of Aeronautics and Astronautics Inc.\n\n\n\n
\n\n\n\n \n \n \"FirePaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{panesi2012,\n\ttitle = {Fire {II} {Flight} {Experiment} {Analysis} by {Means} of a {Collisional}-{Radiative} {Model}},\n\tvolume = {23},\n\turl = {https://arc.aiaa.org/doi/abs/10.2514/1.39034},\n\tdoi = {10.2514/1.39034},\n\tabstract = {We study the behavior of the excited electronic states of atoms in the relaxation zone of one-dimensional airflows obtained in shock-tube facilities. A collisional-radiative model is developed, accounting for thermal nonequilibrium between the translational energy mode of the gas and the vibrational energy mode of individual molecules. The electronic states of atoms are treated as separate species, allowing for non-Boltzmann distributions of their populations. Relaxation of the free-electron energy is also accounted for by using a separate conservation equation. We apply the model to three trajectory points of the Fire II flight experiment. In the rapidly ionizing regime behind strong shock waves, the electronic energy level populations depart from Boltzmann distributions because the highlying bound electronic states are depleted. To quantify the extent of this nonequilibrium effect, we compare the results obtained by means of the collisional-radiative model with those based on Boltzmann distributions. For the earliest trajectory point, we show that the quasi-steady-state assumption is only valid for the high-lying excited states and cannot be extended to the metastable states. © 2008 by the American Institute of Aeronautics and Astronautics, Inc.},\n\tnumber = {2},\n\tjournal = {Journal of Thermophysics and Heat Transfer},\n\tauthor = {Panesi, Marco and Magin, Thierry and Bourdon, Anne and Bultel, Arnaud and Chazot, O.},\n\tmonth = may,\n\tyear = {2012},\n\tnote = {Publisher: American Institute of Aeronautics and Astronautics Inc.},\n\tkeywords = {Degree of Ionization, Energy Distribution, Flow Characteristics, Freestream, One Dimensional Flow, Quasi Steady States, Rankine Hugoniot Relation, Shock Layers, Spontaneous Emission, Thermal Nonequilibrium},\n\tpages = {236--248},\n}\n\n\n\n
\n
\n\n\n
\n We study the behavior of the excited electronic states of atoms in the relaxation zone of one-dimensional airflows obtained in shock-tube facilities. A collisional-radiative model is developed, accounting for thermal nonequilibrium between the translational energy mode of the gas and the vibrational energy mode of individual molecules. The electronic states of atoms are treated as separate species, allowing for non-Boltzmann distributions of their populations. Relaxation of the free-electron energy is also accounted for by using a separate conservation equation. We apply the model to three trajectory points of the Fire II flight experiment. In the rapidly ionizing regime behind strong shock waves, the electronic energy level populations depart from Boltzmann distributions because the highlying bound electronic states are depleted. To quantify the extent of this nonequilibrium effect, we compare the results obtained by means of the collisional-radiative model with those based on Boltzmann distributions. For the earliest trajectory point, we show that the quasi-steady-state assumption is only valid for the high-lying excited states and cannot be extended to the metastable states. © 2008 by the American Institute of Aeronautics and Astronautics, Inc.\n
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\n \n\n \n \n Stern, E. C.; Gidzak, V. M.; and Candler, G. V.\n\n\n \n \n \n \n \n Estimation of dynamic stability coefficients for aerodynamic decelerators using CFD.\n \n \n \n \n\n\n \n\n\n\n In pages 2217–2230, 2012. AIAA Paper 2012-3225\n \n\n\n\n
\n\n\n\n \n \n \"EstimationPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{stern2012,\n\ttitle = {Estimation of dynamic stability coefficients for aerodynamic decelerators using {CFD}},\n\tisbn = {978-1-62410-185-4},\n\turl = {https://arc.aiaa.org/doi/10.2514/6.2012-3225},\n\tdoi = {10.2514/6.2012-3225},\n\tabstract = {A method for performing dynamic simulations of entry vehicles is developed. This capability uses existing infrastructure within the US3D flow solver, developed for doing fluid structure interaction (FSI) simulations, to allow for up to six degree of freedom (6- DoF) simulations. Inviscid, free-to-oscillate simulations of the Mars Science Laboratory (MSL) capsule at Mach 2.5 and 3.5 are used to evaluate different data reduction methods. It is found that many simulations may be required to get reliable data. The computed pitch damping coefficients show comparable trends to ballistic range data, though they differ in magnitude, particularly at high angles of attack. Preliminary viscous simulation results are presented, and show improved agreement with experimental data compared to the inviscid analysis. © 2012 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.},\n\tpublisher = {AIAA Paper 2012-3225},\n\tauthor = {Stern, Eric C. and Gidzak, Vladimyr M. and Candler, Graham V.},\n\tyear = {2012},\n\tpages = {2217--2230},\n}\n\n\n\n
\n
\n\n\n
\n A method for performing dynamic simulations of entry vehicles is developed. This capability uses existing infrastructure within the US3D flow solver, developed for doing fluid structure interaction (FSI) simulations, to allow for up to six degree of freedom (6- DoF) simulations. Inviscid, free-to-oscillate simulations of the Mars Science Laboratory (MSL) capsule at Mach 2.5 and 3.5 are used to evaluate different data reduction methods. It is found that many simulations may be required to get reliable data. The computed pitch damping coefficients show comparable trends to ballistic range data, though they differ in magnitude, particularly at high angles of attack. Preliminary viscous simulation results are presented, and show improved agreement with experimental data compared to the inviscid analysis. © 2012 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.\n
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\n \n\n \n \n Adler, M.; Wright, M.; Campbell, C.; Clark, I.; Engelund, W.; and Rivellini, T.\n\n\n \n \n \n \n Entry, Decent, and Landing Roadmap: Technology Area 9.\n \n \n \n\n\n \n\n\n\n Technical Report 2012.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@techreport{adler2012,\n\ttitle = {Entry, {Decent}, and {Landing} {Roadmap}: {Technology} {Area} 9},\n\tauthor = {Adler, Mark and Wright, Michael and Campbell, Charles and Clark, Ian and Engelund, Walt and Rivellini, Tommaso},\n\tyear = {2012},\n}\n\n\n\n
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\n \n\n \n \n Ibraguimova, L B; Shatalov, O P; and Tunik, Y V\n\n\n \n \n \n \n Equilibrium and non-equilibrium rate constants of oxygen dissociation at high temperatures.\n \n \n \n\n\n \n\n\n\n In volume 1501, pages 1094–1101, 2012. \n Issue: 1\n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{ibraguimova2012,\n\ttitle = {Equilibrium and non-equilibrium rate constants of oxygen dissociation at high temperatures},\n\tvolume = {1501},\n\tauthor = {Ibraguimova, L B and Shatalov, O P and Tunik, Y V},\n\tyear = {2012},\n\tnote = {Issue: 1},\n\tpages = {1094--1101},\n}\n\n\n\n
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\n \n\n \n \n Das, R.\n\n\n \n \n \n \n \n A simulated annealing-based inverse computational fluid dynamics model for unknown parameter estimation in fluid flow problem.\n \n \n \n \n\n\n \n\n\n\n International Journal of Computational Fluid Dynamics, 26(9-10): 499–513. October 2012.\n Publisher: Taylor & Francis\n\n\n\n
\n\n\n\n \n \n \"APaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{das2012,\n\ttitle = {A simulated annealing-based inverse computational fluid dynamics model for unknown parameter estimation in fluid flow problem},\n\tvolume = {26},\n\turl = {https://www.tandfonline.com/doi/abs/10.1080/10618562.2011.632375},\n\tdoi = {10.1080/10618562.2011.632375},\n\tabstract = {In this paper, a simulated annealing (SA)-based optimisation is carried out for simultaneous estimation of the Reynolds number (Re) and the dimensions of the enclosure (lx, ly ) from the knowledge ...},\n\tnumber = {9-10},\n\tjournal = {International Journal of Computational Fluid Dynamics},\n\tauthor = {Das, Ranjan},\n\tmonth = oct,\n\tyear = {2012},\n\tnote = {Publisher: Taylor \\& Francis},\n\tkeywords = {inverse problem, lid-driven cavity flow, simulated annealing, width},\n\tpages = {499--513},\n}\n\n\n\n
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\n In this paper, a simulated annealing (SA)-based optimisation is carried out for simultaneous estimation of the Reynolds number (Re) and the dimensions of the enclosure (lx, ly ) from the knowledge ...\n
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\n  \n 2011\n \n \n (18)\n \n \n
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\n \n\n \n \n Feynman, R. P.; Leinghton B., R.; and Matthew, S.\n\n\n \n \n \n \n The feynman lectures on physics, volume II.\n \n \n \n\n\n \n\n\n\n Basic Books, Millennium edition, 2011.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@book{Feynman2011a,\n\tedition = {Millennium},\n\ttitle = {The feynman lectures on physics, volume {II}},\n\tisbn = {978-0-465-07998-8},\n\tpublisher = {Basic Books},\n\tauthor = {Feynman, Richard P. and Leinghton B., Robert and Matthew, Sands},\n\tyear = {2011},\n}\n\n\n\n
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\n \n\n \n \n Feynman, R. P.; Leighton B., R.; and Matthew, S.\n\n\n \n \n \n \n The feynman lectures on physics, volume III.\n \n \n \n\n\n \n\n\n\n Basic Books, Millennium edition, 2011.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@book{Feynman2011b,\n\tedition = {Millennium},\n\ttitle = {The feynman lectures on physics, volume {III}},\n\tisbn = {978-0-465-02417-9},\n\tpublisher = {Basic Books},\n\tauthor = {Feynman, Richard P. and Leighton B., Robert and Matthew, Sands},\n\tyear = {2011},\n}\n\n\n\n
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\n \n\n \n \n Feynman, R. P.; Leighton B., R.; and Matthew, S.\n\n\n \n \n \n \n The feynman lectures on physics, volume I.\n \n \n \n\n\n \n\n\n\n Basic Books, Millennium edition, 2011.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@book{Feynman2011,\n\tedition = {Millennium},\n\ttitle = {The feynman lectures on physics, volume {I}},\n\tisbn = {978-0-465-02414-8},\n\tpublisher = {Basic Books},\n\tauthor = {Feynman, Richard P. and Leighton B., Robert and Matthew, Sands},\n\tyear = {2011},\n}\n\n\n\n
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\n \n\n \n \n Fruchtman, A.; Zoler, D.; and Makrinich, G.\n\n\n \n \n \n \n \n Potential of an emissive cylindrical probe in plasma.\n \n \n \n \n\n\n \n\n\n\n Physical Review E, 84(2): 025402. August 2011.\n \n\n\n\n
\n\n\n\n \n \n \"PotentialPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{fruchtman2011,\n\ttitle = {Potential of an emissive cylindrical probe in plasma},\n\tvolume = {84},\n\turl = {https://link.aps.org/doi/10.1103/PhysRevE.84.025402},\n\tdoi = {10.1103/PhysRevE.84.025402},\n\tabstract = {The floating potential of an emissive cylindrical probe in a plasma is calculated for an arbitrary ratio of Debye length to probe radius and for an arbitrary ion composition. In their motion to the probe the ions are assumed to be collisionless. For a small Debye length, a two-scale analysis for the quasineutral plasma and for the sheath provides analytical expressions for the emitted and collected currents and for the potential as functions of a generalized mass ratio. For a Debye length that is not small, it is demonstrated that, as the Debye length becomes larger, the probe potential approaches the plasma potential and that the ion density near the probe is not smaller but rather is larger than it is in the plasma bulk.},\n\tnumber = {2},\n\turldate = {2024-04-23},\n\tjournal = {Physical Review E},\n\tauthor = {Fruchtman, A. and Zoler, D. and Makrinich, G.},\n\tmonth = aug,\n\tyear = {2011},\n\tpages = {025402},\n}\n\n\n\n
\n
\n\n\n
\n The floating potential of an emissive cylindrical probe in a plasma is calculated for an arbitrary ratio of Debye length to probe radius and for an arbitrary ion composition. In their motion to the probe the ions are assumed to be collisionless. For a small Debye length, a two-scale analysis for the quasineutral plasma and for the sheath provides analytical expressions for the emitted and collected currents and for the potential as functions of a generalized mass ratio. For a Debye length that is not small, it is demonstrated that, as the Debye length becomes larger, the probe potential approaches the plasma potential and that the ion density near the probe is not smaller but rather is larger than it is in the plasma bulk.\n
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\n \n\n \n \n Jacobson, N. S.; and Myers, D. L.\n\n\n \n \n \n \n Active Oxidation of SiC.\n \n \n \n\n\n \n\n\n\n Oxidation of Metals, 75(1): 1–25. February 2011.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{jacobson_active_2011,\n\ttitle = {Active {Oxidation} of {SiC}},\n\tvolume = {75},\n\tissn = {1573-4889},\n\tdoi = {10.1007/s11085-010-9216-4},\n\tabstract = {Silicon carbide (SiC) forms a protective condensed-phase oxide (SiO2) in passive oxidation and a volatile sub-oxide (SiO(g)) in active oxidation. The transition between these two modes of oxidation and the rates of active oxidation are critical issues. A literature review indicates that impurity effects, the difference between active-to-passive and passive-to-active transitions, and the effect of total pressure on these transitions remain unexplored for SiC. Measurements were made in a thermogravimetric apparatus (TGA) by changing oxygen potentials either by blending O2/Ar mixtures or changing total pressures in a pure oxygen gas stream to the point where a transition occurs. Specimens were examined with standard optical and electron-optical techniques. Active-to-passive and passive-to-active transitions were measured and found to be similar for SiC, which is in contrast to pure Si. The similarity in SiC is attributed to SiC/SiO2 interfacial reactions producing the necessary conditions for passive scale formation (active-to-passive) or passive scale breakdown (passive-to-active). Comparable results were obtained in both the O2/Ar and reduced total O2 pressure cases for SiC.},\n\tlanguage = {en},\n\tnumber = {1},\n\turldate = {2023-10-26},\n\tjournal = {Oxidation of Metals},\n\tauthor = {Jacobson, N. S. and Myers, D. L.},\n\tmonth = feb,\n\tyear = {2011},\n\tkeywords = {Active oxidation, Ceramics, Silicon carbide},\n\tpages = {1--25},\n}\n\n\n\n
\n
\n\n\n
\n Silicon carbide (SiC) forms a protective condensed-phase oxide (SiO2) in passive oxidation and a volatile sub-oxide (SiO(g)) in active oxidation. The transition between these two modes of oxidation and the rates of active oxidation are critical issues. A literature review indicates that impurity effects, the difference between active-to-passive and passive-to-active transitions, and the effect of total pressure on these transitions remain unexplored for SiC. Measurements were made in a thermogravimetric apparatus (TGA) by changing oxygen potentials either by blending O2/Ar mixtures or changing total pressures in a pure oxygen gas stream to the point where a transition occurs. Specimens were examined with standard optical and electron-optical techniques. Active-to-passive and passive-to-active transitions were measured and found to be similar for SiC, which is in contrast to pure Si. The similarity in SiC is attributed to SiC/SiO2 interfacial reactions producing the necessary conditions for passive scale formation (active-to-passive) or passive scale breakdown (passive-to-active). Comparable results were obtained in both the O2/Ar and reduced total O2 pressure cases for SiC.\n
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\n \n\n \n \n Babinsky, H.; and Harvey, J.\n\n\n \n \n \n \n Shock wave-boundary-layer interactions.\n \n \n \n\n\n \n\n\n\n Cambridge University Press, 2011.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@book{babinsky2011,\n\ttitle = {Shock wave-boundary-layer interactions},\n\tpublisher = {Cambridge University Press},\n\tauthor = {Babinsky, Holger and Harvey, John},\n\tyear = {2011},\n}\n\n\n\n\n\n\n\n
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\n \n\n \n \n Stemmer, C\n\n\n \n \n \n \n Investigations on the instability of hypersonic boundary layers, taking into account high-temperature effects.\n \n \n \n\n\n \n\n\n\n Ph.D. Thesis, Technical University of Munich, 2011.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@phdthesis{stemmer2011,\n\ttitle = {Investigations on the instability of hypersonic boundary layers, taking into account high-temperature effects},\n\tschool = {Technical University of Munich},\n\tauthor = {Stemmer, C},\n\tyear = {2011},\n}\n\n\n\n
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\n \n\n \n \n Culler, A. J.; and McNamara, J. J.\n\n\n \n \n \n \n Impact of Fluid-Thermal-Structural Coupling on Response Prediction of Hypersonic Skin Panels.\n \n \n \n\n\n \n\n\n\n AIAA Journal, 49(11): 2393–2406. 2011.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@article{culler2011,\n\ttitle = {Impact of {Fluid}-{Thermal}-{Structural} {Coupling} on {Response} {Prediction} of {Hypersonic} {Skin} {Panels}},\n\tvolume = {49},\n\tissn = {0001-1452},\n\tdoi = {10.2514/1.J050617},\n\tnumber = {11},\n\turldate = {2023-08-03},\n\tjournal = {AIAA Journal},\n\tauthor = {Culler, Adam J. and McNamara, Jack J.},\n\tyear = {2011},\n\tpages = {2393--2406},\n}\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n
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\n \n\n \n \n McNamara, J. J.; and Friedmann, P. P.\n\n\n \n \n \n \n Aeroelastic and Aerothermoelastic Analysis in Hypersonic Flow: Past, Present, and Future.\n \n \n \n\n\n \n\n\n\n AIAA Journal, 49(6): 1089–1122. June 2011.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
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@article{mcnamara2011,\n\ttitle = {Aeroelastic and {Aerothermoelastic} {Analysis} in {Hypersonic} {Flow}: {Past}, {Present}, and {Future}},\n\tvolume = {49},\n\tissn = {0001-1452},\n\tshorttitle = {Aeroelastic and {Aerothermoelastic} {Analysis} in {Hypersonic} {Flow}},\n\tdoi = {10.2514/1.J050882},\n\tnumber = {6},\n\turldate = {2023-08-03},\n\tjournal = {AIAA Journal},\n\tauthor = {McNamara, Jack J. and Friedmann, Peretz P.},\n\tmonth = jun,\n\tyear = {2011},\n\tkeywords = {Aerodynamic Center, Aeroelastic Stability, Arbitrary Lagrangian Eulerian, CFD Analysis, Hypersonic Aerothermodynamics, Hypersonic Vehicles, Inviscid Hypersonic Flow, Orbital Sciences Corporation, Turbomachinery, Wind Turbine Aerodynamics},\n\tpages = {1089--1122},\n}\n\n\n\n
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\n \n\n \n \n Gnoffo, P. A; Berry, S. A; and Van Norman, J. W\n\n\n \n \n \n \n Uncertainty Assessments of 2D and Axisymmetric Hypersonic Shock Wave-Turbulent Boundary Layer Interaction Simulations at Compression Corners.\n \n \n \n\n\n \n\n\n\n In 2011. \n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{gnoffo2011,\n\ttitle = {Uncertainty {Assessments} of {2D} and {Axisymmetric} {Hypersonic} {Shock} {Wave}-{Turbulent} {Boundary} {Layer} {Interaction} {Simulations} at {Compression} {Corners}},\n\tdoi = {10.2514/6.2011-3142},\n\tabstract = {This paper is one of a series of five papers in a special session organized by the NASA Fundamental Aeronautics Program that addresses uncertainty assessments for CFD simulations in hypersonic flow. Simulations of a shock emanating from a compression corner and interacting with a fully developed turbulent boundary layer are evaluated herein. Mission relevant conditions at Mach 7 and Mach 14 are defined for a pre-compression ramp of a scramjet powered vehicle. Three compression angles are defined-the smallest to avoid separation losses and the largest to force a separated flow engaging more complicated flow physics. The Baldwin-Lomax and the Cebeci-Smith algebraic models, the one-equation Spalart-Allmaras model with the Catrix-Aupoix compressibility modification and two-equation models including Menter SST, Wilcox k − ω 98, and Wilcox k − ω 06 turbulence models are evaluated. Each model is fully defined herein to preclude any ambiguity regarding model implementation. Comparisons are made to existing experimental data and Van Driest theory to provide preliminary assessment of model form uncertainty. A set of coarse grained uncertainty metrics are defined to capture essential differences among turbulence models. Except for the inability of algebraic models to converge for some separated flows there is no clearly superior model as judged by these metrics. A preliminary metric for the numerical component of uncertainty in shock-turbulent-boundary-layer interactions at compression corners sufficiently steep to cause separation is defined as 55\\%. This value is a median of differences with experimental data averaged for peak pressure and heating and for extent of separation captured in new, grid-converged solutions presented here. This value is consistent with existing results in a literature review of hypersonic shock-turbulent-boundary-layer interactions by Roy and Blottner and with more recent computations of MacLean.},\n\tauthor = {Gnoffo, Peter A and Berry, Scott A and Van Norman, John W},\n\tyear = {2011},\n}\n\n\n\n
\n
\n\n\n
\n This paper is one of a series of five papers in a special session organized by the NASA Fundamental Aeronautics Program that addresses uncertainty assessments for CFD simulations in hypersonic flow. Simulations of a shock emanating from a compression corner and interacting with a fully developed turbulent boundary layer are evaluated herein. Mission relevant conditions at Mach 7 and Mach 14 are defined for a pre-compression ramp of a scramjet powered vehicle. Three compression angles are defined-the smallest to avoid separation losses and the largest to force a separated flow engaging more complicated flow physics. The Baldwin-Lomax and the Cebeci-Smith algebraic models, the one-equation Spalart-Allmaras model with the Catrix-Aupoix compressibility modification and two-equation models including Menter SST, Wilcox k − ω 98, and Wilcox k − ω 06 turbulence models are evaluated. Each model is fully defined herein to preclude any ambiguity regarding model implementation. Comparisons are made to existing experimental data and Van Driest theory to provide preliminary assessment of model form uncertainty. A set of coarse grained uncertainty metrics are defined to capture essential differences among turbulence models. Except for the inability of algebraic models to converge for some separated flows there is no clearly superior model as judged by these metrics. A preliminary metric for the numerical component of uncertainty in shock-turbulent-boundary-layer interactions at compression corners sufficiently steep to cause separation is defined as 55%. This value is a median of differences with experimental data averaged for peak pressure and heating and for extent of separation captured in new, grid-converged solutions presented here. This value is consistent with existing results in a literature review of hypersonic shock-turbulent-boundary-layer interactions by Roy and Blottner and with more recent computations of MacLean.\n
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\n \n\n \n \n Bowcutt, K. G; Smith, T. R; Kothari, A. P; Raghavan, V.; Tarpley, C.; and Livingston, J. W\n\n\n \n \n \n \n The Hypersonic Space and Global Transportation System: A Concept for Routine and Affordable Access to Space.\n \n \n \n\n\n \n\n\n\n In San Francisco, CA, 2011. \\AIAA Paper\\ 2011-2295\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{bowcutt2011,\n\taddress = {San Francisco, CA},\n\ttitle = {The {Hypersonic} {Space} and {Global} {Transportation} {System}: {A} {Concept} for {Routine} and {Affordable} {Access} to {Space}},\n\tpublisher = {\\{AIAA Paper\\} 2011-2295},\n\tauthor = {Bowcutt, Kevin G and Smith, Thomas R and Kothari, Ajay P and Raghavan, Venkataraman and Tarpley, Christopher and Livingston, John W},\n\tyear = {2011},\n}\n\n\n\n
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\n \n\n \n \n Kim, S W; Shimoyama, T; and Hosono, H\n\n\n \n \n \n \n Solvated Electrons in High-Temperature Melts and Glasses of the Room-Temperature Stable Electride [\\Ca\\\\textsubscript\\24\\\\Al\\\\textsubscript\\28\\\\O\\\\textsubscript\\64\\]\\textsuperscript\\4+\\ 4 e\\textsuperscript\\-\\.\n \n \n \n\n\n \n\n\n\n Science, 333(6038): 71–74. 2011.\n \n\n\n\n
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\n 
@article{kim2011,\n\ttitle = {Solvated {Electrons} in {High}-{Temperature} {Melts} and {Glasses} of the {Room}-{Temperature} {Stable} {Electride} [\\{{Ca}\\}{\\textbackslash}textsubscript\\{24\\}\\{{Al}\\}{\\textbackslash}textsubscript\\{28\\}\\{{O}\\}{\\textbackslash}textsubscript\\{64\\}]{\\textbackslash}textsuperscript\\{4+\\} 4 e{\\textbackslash}textsuperscript\\{-\\}},\n\tvolume = {333},\n\tnumber = {6038},\n\tjournal = {Science},\n\tauthor = {Kim, S W and Shimoyama, T and Hosono, H},\n\tyear = {2011},\n\tpages = {71--74},\n}\n\n\n\n
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\n \n\n \n \n Bruce Owens, D.; and Aubuchon, V. V.\n\n\n \n \n \n \n \n Overview of orion crew module and launch abort vehicle dynamic stability.\n \n \n \n \n\n\n \n\n\n\n In 2011. AIAA Paper 2011-3504\n \n\n\n\n
\n\n\n\n \n \n \"OverviewPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{bruceowens2011,\n\ttitle = {Overview of orion crew module and launch abort vehicle dynamic stability},\n\tisbn = {978-1-62410-145-8},\n\turl = {https://arc.aiaa.org/doi/10.2514/6.2011-3504},\n\tdoi = {10.2514/6.2011-3504},\n\tabstract = {With the retirement of the Space Shuttle, NASA is designing a new spacecraft, called Orion, to fly astronauts to low earth orbit and beyond. Characterization of the dynamic stability of the Orion spacecraft is important for the design of the spacecraft and trajectory construction. Dynamic stability affects the stability and control of the Orion Crew Module during re-entry, especially below Mach = 2.0 and including flight under the drogues. The Launch Abort Vehicle is affected by dynamic stability as well, especially during the re-orientation and heatshield forward segments of the flight. The dynamic stability was assessed using the forced oscillation technique, free-to-oscillate, ballistic range, and sub-scale free-flight tests. All of the test techniques demonstrated that in heatshield-forward flight the Crew Module and Launch Abort Vehicle are dynamically unstable in a significant portion of their flight trajectory. This paper will provide a brief overview of the Orion dynamic aero program and a high-level summary of the dynamic stability characteristics of the Orion spacecraft.},\n\tpublisher = {AIAA Paper 2011-3504},\n\tauthor = {Bruce Owens, D. and Aubuchon, Vanessa V.},\n\tyear = {2011},\n}\n\n\n\n
\n
\n\n\n
\n With the retirement of the Space Shuttle, NASA is designing a new spacecraft, called Orion, to fly astronauts to low earth orbit and beyond. Characterization of the dynamic stability of the Orion spacecraft is important for the design of the spacecraft and trajectory construction. Dynamic stability affects the stability and control of the Orion Crew Module during re-entry, especially below Mach = 2.0 and including flight under the drogues. The Launch Abort Vehicle is affected by dynamic stability as well, especially during the re-orientation and heatshield forward segments of the flight. The dynamic stability was assessed using the forced oscillation technique, free-to-oscillate, ballistic range, and sub-scale free-flight tests. All of the test techniques demonstrated that in heatshield-forward flight the Crew Module and Launch Abort Vehicle are dynamically unstable in a significant portion of their flight trajectory. This paper will provide a brief overview of the Orion dynamic aero program and a high-level summary of the dynamic stability characteristics of the Orion spacecraft.\n
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\n \n\n \n \n Glass, D. E.\n\n\n \n \n \n \n Physical challenges and limitations confronting the use of UHTCs on hypersonic vehicles.\n \n \n \n\n\n \n\n\n\n In 2011. AIAA Paper 2011-2304\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{glass2011,\n\ttitle = {Physical challenges and limitations confronting the use of {UHTCs} on hypersonic vehicles},\n\tdoi = {10.2514/6.2011-2304},\n\tabstract = {Ultra-high temperature ceramics (UHTCs) have been studied for many years as possible material solutions for leading edges of hypersonic vehicles. Over that time, many of the processing and engineering challenges have been addressed. Though UHTCs may have high-temperature capability for some applications, there still remain several physical challenges and limitations confronting their use on hypersonic vehicles. UHTCs possess a very high density, and for weight sensitive vehicles, high density can lead to significant weight concerns. Being monolithic ceramics, UHTCs have thermal shock and fracture toughness concerns that confront all non-fiber-reinforced ceramics. The limitation discussed here for UHTCs is high-temperature oxidation in flight environments. In the temperature range of {\\textasciitilde}2900°F ({\\textasciitilde}1600°C) and below, Si-based UHTCs form a protective silica (SiO2) layer that helps protect the substrate from oxidation. Above that temperature range, Si-based UHTCs appear to experience similar active oxidation issues that confront structural ceramic matrix composites (CMC) such as C/SiC and coated C/C. Non-Si-based materials should be considered to realize a true step forward in temperature capability with respect to conventional Si-based CMCs.},\n\tpublisher = {AIAA Paper 2011-2304},\n\tauthor = {Glass, David E.},\n\tyear = {2011},\n}\n\n\n\n
\n
\n\n\n
\n Ultra-high temperature ceramics (UHTCs) have been studied for many years as possible material solutions for leading edges of hypersonic vehicles. Over that time, many of the processing and engineering challenges have been addressed. Though UHTCs may have high-temperature capability for some applications, there still remain several physical challenges and limitations confronting their use on hypersonic vehicles. UHTCs possess a very high density, and for weight sensitive vehicles, high density can lead to significant weight concerns. Being monolithic ceramics, UHTCs have thermal shock and fracture toughness concerns that confront all non-fiber-reinforced ceramics. The limitation discussed here for UHTCs is high-temperature oxidation in flight environments. In the temperature range of ~2900°F (~1600°C) and below, Si-based UHTCs form a protective silica (SiO2) layer that helps protect the substrate from oxidation. Above that temperature range, Si-based UHTCs appear to experience similar active oxidation issues that confront structural ceramic matrix composites (CMC) such as C/SiC and coated C/C. Non-Si-based materials should be considered to realize a true step forward in temperature capability with respect to conventional Si-based CMCs.\n
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\n \n\n \n \n McGuire, M. K.; Arnold, J. O; Covington, M A.; and Dupzyk, I. C\n\n\n \n \n \n \n Flexible Ablative Thermal Protection Sizing on Inflatable Aerodynamic Decelerator for Human Mars Entry Descent and Landing.\n \n \n \n\n\n \n\n\n\n In Orlando, FL, 2011. \\AIAA Paper\\ 2011-344\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@inproceedings{mcguire2011,\n\taddress = {Orlando, FL},\n\ttitle = {Flexible {Ablative} {Thermal} {Protection} {Sizing} on {Inflatable} {Aerodynamic} {Decelerator} for {Human} {Mars} {Entry} {Descent} and {Landing}},\n\tpublisher = {\\{AIAA Paper\\} 2011-344},\n\tauthor = {McGuire, Mary Kathleen and Arnold, James O and Covington, M Alan and Dupzyk, Iain C},\n\tyear = {2011},\n}\n\n\n\n
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\n \n\n \n \n Sheehan, J P; and Hershkowitz, N\n\n\n \n \n \n \n Emissive probes.\n \n \n \n\n\n \n\n\n\n Plasma Sources Science and Technology, 20(6): 1–22. 2011.\n \n\n\n\n
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@article{sheehan2011,\n\ttitle = {Emissive probes},\n\tvolume = {20},\n\tnumber = {6},\n\tjournal = {Plasma Sources Science and Technology},\n\tauthor = {Sheehan, J P and Hershkowitz, N},\n\tyear = {2011},\n\tpages = {1--22},\n}\n\n\n\n
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\n \n\n \n \n Deschenes, T. R; Holman, T. D; and Boyd, I. D\n\n\n \n \n \n \n Effects of Rotational Energy Relaxation in a Modular Particle-Continuum Method.\n \n \n \n\n\n \n\n\n\n Journal of Thermophysics and Heat Transfer, 25(2): 218–227. 2011.\n \n\n\n\n
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@article{deschenes2011,\n\ttitle = {Effects of {Rotational} {Energy} {Relaxation} in a {Modular} {Particle}-{Continuum} {Method}},\n\tvolume = {25},\n\tnumber = {2},\n\tjournal = {Journal of Thermophysics and Heat Transfer},\n\tauthor = {Deschenes, Timothy R and Holman, Timothy D and Boyd, Iain D},\n\tyear = {2011},\n\tpages = {218--227},\n}\n\n\n\n
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\n \n\n \n \n Maglieri, D. J; Henderson, H. R; Massey, S. J; and Stansbery, E. G\n\n\n \n \n \n \n \n A Compilation of Space Shuttle Sonic Boom Measurements.\n \n \n \n \n\n\n \n\n\n\n Technical Report 2011.\n \n\n\n\n
\n\n\n\n \n \n \"APaper\n  \n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@techreport{maglieri2011,\n\ttitle = {A {Compilation} of {Space} {Shuttle} {Sonic} {Boom} {Measurements}},\n\turl = {http://www.sti.nasa.gov},\n\tauthor = {Maglieri, Domenic J and Henderson, Herbert R and Massey, Steven J and Stansbery, Eugene G},\n\tyear = {2011},\n}\n\n\n\n
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\n  \n 2010\n \n \n (17)\n \n \n
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\n \n\n \n \n \n\n\n \n \n \n \n \n Atlas V Launch Services User's Guide.\n \n \n \n \n\n\n \n\n\n\n March 2010.\n \n\n\n\n
\n\n\n\n \n \n \"AtlasPaper\n  \n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@misc{atlas2010,\n\ttitle = {Atlas {V} {Launch} {Services} {User}'s {Guide}},\n\turl = {https://www.ulalaunch.com/docs/default-source/rockets/atlasvusersguide2010a.pdf?sfvrsn=f84bb59e_2},\n\tmonth = mar,\n\tyear = {2010},\n}\n\n\n\n
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\n \n\n \n \n Culler, A. J.; and McNamara, J. J.\n\n\n \n \n \n \n Studies on Fluid-Thermal-Structural Coupling for Aerothermoelasticity in Hypersonic Flow.\n \n \n \n\n\n \n\n\n\n AIAA Journal, 48(8): 1721–1738. 2010.\n \n\n\n\n
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@article{culler2010,\n\ttitle = {Studies on {Fluid}-{Thermal}-{Structural} {Coupling} for {Aerothermoelasticity} in {Hypersonic} {Flow}},\n\tvolume = {48},\n\tissn = {0001-1452},\n\tdoi = {10.2514/1.J050193},\n\tnumber = {8},\n\turldate = {2023-08-03},\n\tjournal = {AIAA Journal},\n\tauthor = {Culler, Adam J. and McNamara, Jack J.},\n\tyear = {2010},\n\tpages = {1721--1738},\n}\n\n\n\n
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\n \n\n \n \n Tzong, G.; Jacobs, R.; and Liguore, S.\n\n\n \n \n \n \n Predictive Capability for Hypersonic Structural Response and Life Prediction: Phase 1-Identifcation of Knowledge Gaps.\n \n \n \n\n\n \n\n\n\n Technical Report AFRL-RB-WP-TR-2010-3068, 2010.\n \n\n\n\n
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@techreport{tzong2010,\n\ttitle = {Predictive {Capability} for {Hypersonic} {Structural} {Response} and {Life} {Prediction}: {Phase} 1-{Identifcation} of {Knowledge} {Gaps}},\n\tnumber = {AFRL-RB-WP-TR-2010-3068},\n\tauthor = {Tzong, George and Jacobs, Richard and Liguore, Salvatore},\n\tyear = {2010},\n}\n\n\n\n
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\n \n\n \n \n J Mitroy, M S S.; and Clark, C. W\n\n\n \n \n \n \n Theory and applications of atomic and ionic polarizabilities.\n \n \n \n\n\n \n\n\n\n Journal of Physics B: Atomic, Molecular and Optical Physics, 43(20): 202001–202001. October 2010.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@article{jmitroy2010,\n\ttitle = {Theory and applications of atomic and ionic polarizabilities},\n\tvolume = {43},\n\tnumber = {20},\n\tjournal = {Journal of Physics B: Atomic, Molecular and Optical Physics},\n\tauthor = {J Mitroy, M S Safronova and Clark, Charles W},\n\tmonth = oct,\n\tyear = {2010},\n\tpages = {202001--202001},\n}\n\n\n\n
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\n \n\n \n \n McCallumore, K. M.; and Sparapani, E. F.\n\n\n \n \n \n \n The Importance of the Ninth Grade on High School Graduation Rates and Student Success.\n \n \n \n\n\n \n\n\n\n Education Digest: Essential Readings Condensed for Quick Review, 76(2): 60–64. 2010.\n \n\n\n\n
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@article{mccallumore2010,\n\ttitle = {The {Importance} of the {Ninth} {Grade} on {High} {School} {Graduation} {Rates} and {Student} {Success}},\n\tvolume = {76},\n\tnumber = {2},\n\tjournal = {Education Digest: Essential Readings Condensed for Quick Review},\n\tauthor = {McCallumore, Kyle M. and Sparapani, Ervin F.},\n\tyear = {2010},\n\tkeywords = {mccallumore:ed:2010},\n\tpages = {60--64},\n}\n\n\n\n
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\n \n\n \n \n Candler, G. V; Doraiswamy, S.; and Kelley, J D.\n\n\n \n \n \n \n The Potential Role of Electronically-Excited States in Recombining Flows.\n \n \n \n\n\n \n\n\n\n In 2010. \n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{candler2010,\n\ttitle = {The {Potential} {Role} of {Electronically}-{Excited} {States} in {Recombining} {Flows}},\n\tdoi = {10.2514/6.2010-912},\n\tabstract = {Recent experimental measurements in the reflected shock tunnel CUBRC LENS-I facility raise questions about our ability to correctly model oxygen and carbon dioxide re-combination. We consider two possible mechanisms involving the electronically excited states of these molecules that may help explain the experimental data. Oxygen has two low-lying electronically excited states, which have long radiative and collisional lifetimes. We postulate that recombination to these states may help explain the apparent errors in predicting the recombination of oxygen. Carbon dioxide has different behavior and has a single excited state just below the dissociation energy. A recent computational chemistry study shows that CO 2 recombines to this state and then relaxes to the ground electronic state. We propose a simple model to represent the effect of this intermediate state in the recombination process. Preliminary simulations show that this model may help explain part of the puzzling data.},\n\tauthor = {Candler, Graham V and Doraiswamy, Sriram and Kelley, J Daniel},\n\tyear = {2010},\n}\n\n\n\n
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\n Recent experimental measurements in the reflected shock tunnel CUBRC LENS-I facility raise questions about our ability to correctly model oxygen and carbon dioxide re-combination. We consider two possible mechanisms involving the electronically excited states of these molecules that may help explain the experimental data. Oxygen has two low-lying electronically excited states, which have long radiative and collisional lifetimes. We postulate that recombination to these states may help explain the apparent errors in predicting the recombination of oxygen. Carbon dioxide has different behavior and has a single excited state just below the dissociation energy. A recent computational chemistry study shows that CO 2 recombines to this state and then relaxes to the ground electronic state. We propose a simple model to represent the effect of this intermediate state in the recombination process. Preliminary simulations show that this model may help explain part of the puzzling data.\n
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\n \n\n \n \n Office of Chief Scientist\n\n\n \n \n \n \n Technology Horizons: A Vision for Air Force Science and Technology for 2010-30.\n \n \n \n\n\n \n\n\n\n Technical Report 2010.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@techreport{officeofchiefscientist2010,\n\ttitle = {Technology {Horizons}: {A} {Vision} for {Air} {Force} {Science} and {Technology} for 2010-30},\n\tauthor = {{Office of Chief Scientist}},\n\tyear = {2010},\n}\n\n\n\n
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\n \n\n \n \n Dickinson, B.; Singler, J. R; and Abate, G.\n\n\n \n \n \n \n \n Structural Measurements for Enhanced MAV Flight.\n \n \n \n \n\n\n \n\n\n\n In 2010. AIAA 2010-7933\n \n\n\n\n
\n\n\n\n \n \n \"StructuralPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{dickinson2010,\n\ttitle = {Structural {Measurements} for {Enhanced} {MAV} {Flight}},\n\turl = {http://arc.aiaa.org},\n\tdoi = {10.2514/6.2010-7933},\n\tabstract = {Our sense of touch allows us to feel the forces in our limbs when we walk, swim, or hold our arms out the window of a moving car. We anticipate this sense is key in the locomotion of natural flyers. Inspired by the sense of touch, the overall goal of this research is to develop techniques for the estimation of aerodynamic loads from structural measurements for flight control applications. We submit a general algorithm for the direct estimation of distributed steady loads over bodies from embedded noisy deformation-based measurements. The estimation algorithm is applied to a linearly elastic membrane test problem where three applied distributed loads are estimated using three measurement configurations with various amounts of noise. We demonstrate accurate load estimates with simple sensor configurations , despite noisy measurements. Online real-time aerodynamic load estimates may lead to flight control designs that improve the stability and agility of micro air vehicles.},\n\tpublisher = {AIAA 2010-7933},\n\tauthor = {Dickinson, Ben and Singler, John R and Abate, Gregg},\n\tyear = {2010},\n}\n\n\n\n
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\n\n\n
\n Our sense of touch allows us to feel the forces in our limbs when we walk, swim, or hold our arms out the window of a moving car. We anticipate this sense is key in the locomotion of natural flyers. Inspired by the sense of touch, the overall goal of this research is to develop techniques for the estimation of aerodynamic loads from structural measurements for flight control applications. We submit a general algorithm for the direct estimation of distributed steady loads over bodies from embedded noisy deformation-based measurements. The estimation algorithm is applied to a linearly elastic membrane test problem where three applied distributed loads are estimated using three measurement configurations with various amounts of noise. We demonstrate accurate load estimates with simple sensor configurations , despite noisy measurements. Online real-time aerodynamic load estimates may lead to flight control designs that improve the stability and agility of micro air vehicles.\n
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\n \n\n \n \n Shen, G.; and Ge, W.\n\n\n \n \n \n \n \n Simulation of hard-disk flow in microchannels.\n \n \n \n \n\n\n \n\n\n\n Physical Review E - Statistical, Nonlinear, and Soft Matter Physics, 81(1). January 2010.\n Publisher: American Physical Society\n\n\n\n
\n\n\n\n \n \n \"SimulationPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{shen2010,\n\ttitle = {Simulation of hard-disk flow in microchannels},\n\tvolume = {81},\n\turl = {https://journals.aps.org/pre/abstract/10.1103/PhysRevE.81.011201},\n\tdoi = {10.1103/PHYSREVE.81.011201/FIGURES/24/MEDIUM},\n\tabstract = {The dynamic flow behavior of a hard-disk fluid under external force field in two-dimensional microchannels is investigated using an event-driven molecular dynamics simulation method. Simulations have been carried out under laminar and subsonic conditions in both slip regime and transition regime, and the effects of three main factors, Knudsen number (Kn), force field intensity, and packing fraction, on flow and heat transfer behavior have been studied. It is shown that all the factors play important roles in the velocity distribution of the flow, and the temperature profile of the gas flow may exhibit a bimodal shape with a local minimum instead of a maximum in the center. These findings verify the predictions of nonequilibrium kinetic theories on the so-called "temperature dip." At high Kn, the two maxima of temperature shift to two walls and the temperature profile changes to a "parabola" opening upward with a minimum in the center. A slight setback of the temperature is also found before the fluid flow eventually arrives at a steady state when the shear rate is high enough. © 2010 The American Physical Society.},\n\tnumber = {1},\n\tjournal = {Physical Review E - Statistical, Nonlinear, and Soft Matter Physics},\n\tauthor = {Shen, Guofei and Ge, Wei},\n\tmonth = jan,\n\tyear = {2010},\n\tnote = {Publisher: American Physical Society},\n}\n\n\n\n
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\n The dynamic flow behavior of a hard-disk fluid under external force field in two-dimensional microchannels is investigated using an event-driven molecular dynamics simulation method. Simulations have been carried out under laminar and subsonic conditions in both slip regime and transition regime, and the effects of three main factors, Knudsen number (Kn), force field intensity, and packing fraction, on flow and heat transfer behavior have been studied. It is shown that all the factors play important roles in the velocity distribution of the flow, and the temperature profile of the gas flow may exhibit a bimodal shape with a local minimum instead of a maximum in the center. These findings verify the predictions of nonequilibrium kinetic theories on the so-called \"temperature dip.\" At high Kn, the two maxima of temperature shift to two walls and the temperature profile changes to a \"parabola\" opening upward with a minimum in the center. A slight setback of the temperature is also found before the fluid flow eventually arrives at a steady state when the shear rate is high enough. © 2010 The American Physical Society.\n
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\n \n\n \n \n Lamnaouer, M.\n\n\n \n \n \n \n Numerical Modeling of the Shock Tube Flow Fields Before and During Ignition Delay Time Experiments at Practical Conditions.\n \n \n \n\n\n \n\n\n\n . 2010.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{lamnaouer2010,\n\ttitle = {Numerical {Modeling} of the {Shock} {Tube} {Flow} {Fields} {Before} and {During} {Ignition} {Delay} {Time} {Experiments} at {Practical} {Conditions}},\n\tauthor = {Lamnaouer, Mouna},\n\tyear = {2010},\n}\n\n\n\n
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\n \n\n \n \n Nompelis, I.; and Candler, G. V\n\n\n \n \n \n \n Numerical Investigation of DoubleCone Flow Experiments with High-Enthalpy Effects.\n \n \n \n\n\n \n\n\n\n In 2010. \\AIAA Paper\\ 2010-1283\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{nompelis2010,\n\ttitle = {Numerical {Investigation} of {DoubleCone} {Flow} {Experiments} with {High}-{Enthalpy} {Effects}},\n\tpublisher = {\\{AIAA Paper\\} 2010-1283},\n\tauthor = {Nompelis, Ioannis and Candler, Graham V},\n\tyear = {2010},\n}\n\n\n\n
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\n \n\n \n \n Alauzet, F.; and Loseille, A.\n\n\n \n \n \n \n High-order sonic boom modeling based on adaptive methods.\n \n \n \n\n\n \n\n\n\n Journal of Computational Physics, 229(3): 561–593. February 2010.\n Publisher: Academic Press Inc.\n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{alauzet2010,\n\ttitle = {High-order sonic boom modeling based on adaptive methods},\n\tvolume = {229},\n\tdoi = {10.1016/j.jcp.2009.09.020},\n\tabstract = {This paper presents an accurate approach to simulate the sonic boom of supersonic aircrafts. The near-field flow is modeled by the conservative Euler equations and is solved using a vertex-centered finite volume approach on adapted unstructured tetrahedral meshes. A metric-based anisotropic mesh adaptation is considered to control the interpolation error in Lp norm. Then, from the CFD solution, the pressure distribution under the aircraft is extracted and used to set up the initial conditions of the propagation algorithm in the far-field. The pressure distribution is propagated down to the ground in order to obtain the sonic boom signature using a ray tracing algorithm based upon the Thomas waveform parameter method. In this study, a sonic boom sensitivity analysis is carried out on several aircraft designs (low-drag and low-boom shapes). © 2009 Elsevier Inc. All rights reserved.},\n\tnumber = {3},\n\tjournal = {Journal of Computational Physics},\n\tauthor = {Alauzet, F. and Loseille, A.},\n\tmonth = feb,\n\tyear = {2010},\n\tnote = {Publisher: Academic Press Inc.},\n\tkeywords = {Anisotropic mesh adaptation, Euler equations, Finite volume, Sonic boom, Waveform parameter method},\n\tpages = {561--593},\n}\n\n\n\n
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\n This paper presents an accurate approach to simulate the sonic boom of supersonic aircrafts. The near-field flow is modeled by the conservative Euler equations and is solved using a vertex-centered finite volume approach on adapted unstructured tetrahedral meshes. A metric-based anisotropic mesh adaptation is considered to control the interpolation error in Lp norm. Then, from the CFD solution, the pressure distribution under the aircraft is extracted and used to set up the initial conditions of the propagation algorithm in the far-field. The pressure distribution is propagated down to the ground in order to obtain the sonic boom signature using a ray tracing algorithm based upon the Thomas waveform parameter method. In this study, a sonic boom sensitivity analysis is carried out on several aircraft designs (low-drag and low-boom shapes). © 2009 Elsevier Inc. All rights reserved.\n
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\n \n\n \n \n White, M. D.; Morgan, P. E.; and Visbal, M. R.\n\n\n \n \n \n \n \n High fidelity aero-optical analysis.\n \n \n \n \n\n\n \n\n\n\n In 2010. American Institute of Aeronautics and Astronautics Inc.\n \n\n\n\n
\n\n\n\n \n \n \"HighPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{white2010,\n\ttitle = {High fidelity aero-optical analysis},\n\turl = {https://arc.aiaa.org/doi/abs/10.2514/6.2010-433},\n\tdoi = {10.2514/6.2010-433},\n\tabstract = {High-order compact difference methods utilizing implicit Large Eddy Simulation (ILES) and hybrid Reynolds averaged Navier-Stokes (RANS)/ILES are utilized to compute compressible shear layers and flow over a conformal turret in order to examine aero-optical aberrations. The optics are computed with both a high-order parabolic beam solver and traditional aero-optics. The effect of aperture size on the OPDrms is investigated. In the ILES simulation of forced shear layers, it is seen that tip and tilt dominate in the flow structures across all apertures. When the flow is corrected for tip/tilt, the apparent OPD can change dramatically and may give misleading results in terms of structure identification. The results also demonstrate how different density flows can give very similar looking OPD values. The hybrid RANS/ILES turret results also show how aperture sizes can affect the OPDrms. The current calculations do not appear to agree with the tip/tilt corrected rootmean- square of the experiments. However, uncorrected wavefronts do show similar trends to the experimental results. This may point to potential limitations of hybrid approaches due to the lack of large scale structures in the area where RANS is active. © 2010 by the American Institute of Aeronautics and Astronautics, Inc.},\n\tpublisher = {American Institute of Aeronautics and Astronautics Inc.},\n\tauthor = {White, Michael D. and Morgan, Philip E. and Visbal, Miguel R.},\n\tyear = {2010},\n}\n\n\n\n
\n
\n\n\n
\n High-order compact difference methods utilizing implicit Large Eddy Simulation (ILES) and hybrid Reynolds averaged Navier-Stokes (RANS)/ILES are utilized to compute compressible shear layers and flow over a conformal turret in order to examine aero-optical aberrations. The optics are computed with both a high-order parabolic beam solver and traditional aero-optics. The effect of aperture size on the OPDrms is investigated. In the ILES simulation of forced shear layers, it is seen that tip and tilt dominate in the flow structures across all apertures. When the flow is corrected for tip/tilt, the apparent OPD can change dramatically and may give misleading results in terms of structure identification. The results also demonstrate how different density flows can give very similar looking OPD values. The hybrid RANS/ILES turret results also show how aperture sizes can affect the OPDrms. The current calculations do not appear to agree with the tip/tilt corrected rootmean- square of the experiments. However, uncorrected wavefronts do show similar trends to the experimental results. This may point to potential limitations of hybrid approaches due to the lack of large scale structures in the area where RANS is active. © 2010 by the American Institute of Aeronautics and Astronautics, Inc.\n
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\n \n\n \n \n Coirier, W.; and Tramel, R.\n\n\n \n \n \n \n Development of An Integrated Aero-Optics Modeling Capability: OVERFLOW-AeroOptics.\n \n \n \n\n\n \n\n\n\n In Orlando, FL, January 2010. \\AIAA Paper\\ 2010-557\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{coirier2010,\n\taddress = {Orlando, FL},\n\ttitle = {Development of {An} {Integrated} {Aero}-{Optics} {Modeling} {Capability}: {OVERFLOW}-{AeroOptics}},\n\tpublisher = {\\{AIAA Paper\\} 2010-557},\n\tauthor = {Coirier, William and Tramel, Robert},\n\tmonth = jan,\n\tyear = {2010},\n}\n\n\n\n
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\n \n\n \n \n Viana, F. A. C.; Venter, G.; and Balabanov, V.\n\n\n \n \n \n \n \n An algorithm for fast optimal Latin hypercube design of experiments.\n \n \n \n \n\n\n \n\n\n\n International Journal for Numerical Methods in Engineering, 82(2): 135–156. 2010.\n Publisher: John Wiley & Sons, Ltd\n\n\n\n
\n\n\n\n \n \n \"AnPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{viana2010,\n\ttitle = {An algorithm for fast optimal {Latin} hypercube design of experiments},\n\tvolume = {82},\n\turl = {https://onlinelibrary.wiley.com/doi/full/10.1002/nme.2750},\n\tdoi = {10.1002/NME.2750},\n\tabstract = {This paper presents the translational propagation algorithm, a new method for obtaining optimal or near optimal Latin hypercube designs (LHDs) without using formal optimization. The procedure requires minimal computational effort with results virtually provided in real time. The algorithm exploits patterns of point locations for optimal LHDs based on the Φp criterion (a variation of the maximum distance criterion). Small building blocks, consisting of one or more points each, are used to recreate these patterns by simple translation in the hyperspace. Monte Carlo simulations were used to evaluate the performance of the new algorithm for different design configurations where both the dimensionality and the point density were studied. The proposed algorithm was also compared against three formal optimization approaches (namely random search, genetic algorithm, and enhanced stochastic evolutionary algorithm). It was found that (i) the distribution of the Φp values tends to lower values as the dimensionality is increased and (ii) the proposed translational propagation algorithm represents a computationally attractive strategy to obtain near optimum LHDs up to medium dimensions. © 2009 John Wiley \\& Sons, Ltd.},\n\tnumber = {2},\n\tjournal = {International Journal for Numerical Methods in Engineering},\n\tauthor = {Viana, Felipe A. C. and Venter, Gerhard and Balabanov, Vladimir},\n\tyear = {2010},\n\tnote = {Publisher: John Wiley \\& Sons, Ltd},\n\tkeywords = {Latin hypercube sampling, design of computer experiments, experimental design, translational propagation algorithm},\n\tpages = {135--156},\n}\n\n\n\n
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\n\n\n
\n This paper presents the translational propagation algorithm, a new method for obtaining optimal or near optimal Latin hypercube designs (LHDs) without using formal optimization. The procedure requires minimal computational effort with results virtually provided in real time. The algorithm exploits patterns of point locations for optimal LHDs based on the Φp criterion (a variation of the maximum distance criterion). Small building blocks, consisting of one or more points each, are used to recreate these patterns by simple translation in the hyperspace. Monte Carlo simulations were used to evaluate the performance of the new algorithm for different design configurations where both the dimensionality and the point density were studied. The proposed algorithm was also compared against three formal optimization approaches (namely random search, genetic algorithm, and enhanced stochastic evolutionary algorithm). It was found that (i) the distribution of the Φp values tends to lower values as the dimensionality is increased and (ii) the proposed translational propagation algorithm represents a computationally attractive strategy to obtain near optimum LHDs up to medium dimensions. © 2009 John Wiley & Sons, Ltd.\n
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\n \n\n \n \n McNamara, J. J; Crowell, A. R; Friedmann, P. P; Glaz, B.; and Gogulapati, A.\n\n\n \n \n \n \n \n Approximate Modeling of Unsteady Aerodynamics for Hypersonic Aeroelasticity.\n \n \n \n \n\n\n \n\n\n\n Journal of Aircraft, 47(6). 2010.\n \n\n\n\n
\n\n\n\n \n \n \"ApproximatePaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{mcnamara2010,\n\ttitle = {Approximate {Modeling} of {Unsteady} {Aerodynamics} for {Hypersonic} {Aeroelasticity}},\n\tvolume = {47},\n\turl = {http://arc.aiaa.org},\n\tdoi = {10.2514/1.C000190},\n\tabstract = {Various approximations to unsteady aerodynamics are examined for the aeroelastic analysis of a thin double-wedge airfoil in hypersonic flow. Flutter boundaries are obtained using classical hypersonic unsteady aerodynamic theories: piston theory, Van Dyke's second-order theory, Newtonian impact theory, and unsteady shock-expansion theory. The theories are evaluated by comparing the flutter boundaries with those predicted using computational fluid dynamics solutions to the unsteady Navier-Stokes equations. In addition, several alternative approaches to the classical approximations are also evaluated: two different viscous approximations based on effective shapes and combined approximate computational approaches that use steady-state computational-fluid-dynamics-based surrogate models in conjunction with piston theory. The results indicate that, with the exception of first-order piston theory and Newtonian impact theory, the approximate theories yield predictions between 3 and 17\\% of normalized root-mean-square error and between 7 and 40\\% of normalized maximum error of the unsteady Navier-Stokes predictions. Furthermore, the demonstrated accuracy of the combined steady-state computational fluid dynamics and piston theory approaches suggest that important nonlinearities in hypersonic flow are primarily due to steady-state effects. This implies that steady-state flow analysis may be an alternative to time-accurate Navier-Stokes solutions for capturing complex flow effects. Nomenclature fA p g = estimated aeroelastic system matrix a = nondimensional offset between the elastic axis and the midchord, positive for elastic-axis locations behind midchord a o , a i , b i , A i = coefficients used for damping and frequency identification a 1 = speed of sound b = semichord, c=2† Cx† = local deviations of kriging model C L;SS , C L;SUR SS = static component of lift coefficient computed using a computational fluid dynamics and a computational-fluid-dynamics-based surrogate C M;SS , C M;SUR SS = static component of moment coefficient about the midchord computed using a computational fluid dynamics and a computational-fluid-dynamics-based surrogate C p = pressure coefficient fC p g = estimated aeroelastic system matrix C p = component of piston theory pressure due to combined surface velocity and surface inclination C p;SS = component of piston theory pressure due strictly to surface inclination C p;vel = component of piston theory pressure due strictly to surface velocity c = chord length, reference length c l , c m = coefficients of lift and moment about the elastic axis F Z = flutter prediction parameter F j† = intermediate function used to compute the flutter prediction parameter h = plunge degree of freedom of the airfoil h i = states in state-space representation of autoregressive model K = diagonal generalized stiffness matrix K h , K = spring constants in pitch and plunge k = discrete time L = sectional lift force L 1 = normalized maximum error M = diagonal generalized mass matrix M EA = sectional aerodynamic moment about the elastic axis M f = flutter Mach number M 1 = freestream Mach number m = Mass n m = number of modes p, p 1 = pressure and freestream pressure Q = vector of generalized forces q = vector of generalized degrees of freedom q i = generalized displacements q 1 , q f = dynamic pressure and dynamic pressure at flutter R = gas constant for air Rx† = global approximation of kriging model r = real part of eigenvalue r = nondimensional radius of gyration of the airfoil S = sample sites of the parameter space S = airfoil static imbalance s = imaginary part of eigenvalue T e = sample time t = time = freestream velocity v n = normal velocity of airfoil surfaces W = snapshot matrix, computational fluid dynamics response data to s w d = displacement of the surface of the structure X j , Y j = flutter parameter matrices fX p g = state matrix x, y, z = spatial coordinates x rot = point about which airfoil angle of attack is measured x = nondimensional offset between the elastic axis and the cross-sectional center of gravity yx† = kriging approximation Zx; t† = position of structural surface Z str x† = function describing surface geometry = pitch degree of freedom s = angle of attack = ratio of specific heats k1 = input for autoregressive moving-average model of aeroelastic system = damping ratio = estimated matrix eigenvalue m = airfoil mass ratio = air density = slope of the airfoil surface i = vector of displacements for mode i ! = frequency ! h = frequency corresponding to stiffness associated with the plunge degree of freedom of the airfoil ! = frequency corresponding to stiffness associated with the pitch degree of freedom of the airfoil},\n\tnumber = {6},\n\tjournal = {Journal of Aircraft},\n\tauthor = {McNamara, Jack J and Crowell, Andrew R and Friedmann, Peretz P and Glaz, Bryan and Gogulapati, Abhijit},\n\tyear = {2010},\n}\n\n\n\n
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\n Various approximations to unsteady aerodynamics are examined for the aeroelastic analysis of a thin double-wedge airfoil in hypersonic flow. Flutter boundaries are obtained using classical hypersonic unsteady aerodynamic theories: piston theory, Van Dyke's second-order theory, Newtonian impact theory, and unsteady shock-expansion theory. The theories are evaluated by comparing the flutter boundaries with those predicted using computational fluid dynamics solutions to the unsteady Navier-Stokes equations. In addition, several alternative approaches to the classical approximations are also evaluated: two different viscous approximations based on effective shapes and combined approximate computational approaches that use steady-state computational-fluid-dynamics-based surrogate models in conjunction with piston theory. The results indicate that, with the exception of first-order piston theory and Newtonian impact theory, the approximate theories yield predictions between 3 and 17% of normalized root-mean-square error and between 7 and 40% of normalized maximum error of the unsteady Navier-Stokes predictions. Furthermore, the demonstrated accuracy of the combined steady-state computational fluid dynamics and piston theory approaches suggest that important nonlinearities in hypersonic flow are primarily due to steady-state effects. This implies that steady-state flow analysis may be an alternative to time-accurate Navier-Stokes solutions for capturing complex flow effects. Nomenclature fA p g = estimated aeroelastic system matrix a = nondimensional offset between the elastic axis and the midchord, positive for elastic-axis locations behind midchord a o , a i , b i , A i = coefficients used for damping and frequency identification a 1 = speed of sound b = semichord, c=2† Cx† = local deviations of kriging model C L;SS , C L;SUR SS = static component of lift coefficient computed using a computational fluid dynamics and a computational-fluid-dynamics-based surrogate C M;SS , C M;SUR SS = static component of moment coefficient about the midchord computed using a computational fluid dynamics and a computational-fluid-dynamics-based surrogate C p = pressure coefficient fC p g = estimated aeroelastic system matrix C p = component of piston theory pressure due to combined surface velocity and surface inclination C p;SS = component of piston theory pressure due strictly to surface inclination C p;vel = component of piston theory pressure due strictly to surface velocity c = chord length, reference length c l , c m = coefficients of lift and moment about the elastic axis F Z = flutter prediction parameter F j† = intermediate function used to compute the flutter prediction parameter h = plunge degree of freedom of the airfoil h i = states in state-space representation of autoregressive model K = diagonal generalized stiffness matrix K h , K = spring constants in pitch and plunge k = discrete time L = sectional lift force L 1 = normalized maximum error M = diagonal generalized mass matrix M EA = sectional aerodynamic moment about the elastic axis M f = flutter Mach number M 1 = freestream Mach number m = Mass n m = number of modes p, p 1 = pressure and freestream pressure Q = vector of generalized forces q = vector of generalized degrees of freedom q i = generalized displacements q 1 , q f = dynamic pressure and dynamic pressure at flutter R = gas constant for air Rx† = global approximation of kriging model r = real part of eigenvalue r = nondimensional radius of gyration of the airfoil S = sample sites of the parameter space S = airfoil static imbalance s = imaginary part of eigenvalue T e = sample time t = time = freestream velocity v n = normal velocity of airfoil surfaces W = snapshot matrix, computational fluid dynamics response data to s w d = displacement of the surface of the structure X j , Y j = flutter parameter matrices fX p g = state matrix x, y, z = spatial coordinates x rot = point about which airfoil angle of attack is measured x = nondimensional offset between the elastic axis and the cross-sectional center of gravity yx† = kriging approximation Zx; t† = position of structural surface Z str x† = function describing surface geometry = pitch degree of freedom s = angle of attack = ratio of specific heats k1 = input for autoregressive moving-average model of aeroelastic system = damping ratio = estimated matrix eigenvalue m = airfoil mass ratio = air density = slope of the airfoil surface i = vector of displacements for mode i ! = frequency ! h = frequency corresponding to stiffness associated with the plunge degree of freedom of the airfoil ! = frequency corresponding to stiffness associated with the pitch degree of freedom of the airfoil\n
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\n \n\n \n \n Holden, M. S; Wadhams, T. P; and MacLean, M.\n\n\n \n \n \n \n A Review of Experimental Studies with the Double Cone and Hollow Cylinder/Flare Configurations in the LENS Hypervelocity Tunnels and Comparisons with Navier-Stokes and DSMC Computations.\n \n \n \n\n\n \n\n\n\n In Orlando, FL, 2010. \\AIAA Paper\\ 2010-1281\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{holden2010,\n\taddress = {Orlando, FL},\n\ttitle = {A {Review} of {Experimental} {Studies} with the {Double} {Cone} and {Hollow} {Cylinder}/{Flare} {Configurations} in the {LENS} {Hypervelocity} {Tunnels} and {Comparisons} with {Navier}-{Stokes} and {DSMC} {Computations}},\n\tpublisher = {\\{AIAA Paper\\} 2010-1281},\n\tauthor = {Holden, Michael S and Wadhams, Timothy P and MacLean, Matthew},\n\tyear = {2010},\n}\n\n\n\n
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\n  \n 2009\n \n \n (16)\n \n \n
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\n \n\n \n \n Coleman, H.; and Steele, W. G.\n\n\n \n \n \n \n Experimentation, Validation, and Uncertainty Analysis for Engineers.\n \n \n \n\n\n \n\n\n\n John Wiley & Sons, 2009.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@book{coleman2009,\n\ttitle = {Experimentation, {Validation}, and {Uncertainty} {Analysis} for {Engineers}},\n\tpublisher = {John Wiley \\& Sons},\n\tauthor = {Coleman, Hugh and Steele, W. Glenn},\n\tyear = {2009},\n}\n\n\n\n
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\n \n\n \n \n Perepezko, J. H.\n\n\n \n \n \n \n The hotter the engine, the better.\n \n \n \n\n\n \n\n\n\n Science, 326(5956): 1068–1069. November 2009.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{perepezko2009,\n\ttitle = {The hotter the engine, the better},\n\tvolume = {326},\n\tdoi = {10.1126/science.1179327},\n\tabstract = {Alloys based on molybdenum or niobium may allow the high-temperature components of jet engines to run hotter and more efficiently.},\n\tnumber = {5956},\n\tjournal = {Science},\n\tauthor = {Perepezko, John H.},\n\tmonth = nov,\n\tyear = {2009},\n\tpages = {1068--1069},\n}\n\n\n\n
\n
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\n Alloys based on molybdenum or niobium may allow the high-temperature components of jet engines to run hotter and more efficiently.\n
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\n \n\n \n \n Liu, C.; Yang, Y.; Zhang, R.; and Luo, X.\n\n\n \n \n \n \n \n Grain growth simulation of \\111\\ and \\110\\ oriented CVD–SiC film by Potts Monte Carlo.\n \n \n \n \n\n\n \n\n\n\n Computational Materials Science, 44(4): 1281–1285. February 2009.\n \n\n\n\n
\n\n\n\n \n \n \"GrainPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{liu_grain_2009,\n\ttitle = {Grain growth simulation of \\{111\\} and \\{110\\} oriented {CVD}–{SiC} film by {Potts} {Monte} {Carlo}},\n\tvolume = {44},\n\tissn = {0927-0256},\n\turl = {https://www.sciencedirect.com/science/article/pii/S0927025608004011},\n\tdoi = {10.1016/j.commatsci.2008.08.026},\n\tabstract = {In analyzing microstructure evolution of material, study for the process of grain growth is both theoretically and practically significant. On (111) and (110) facets, the process of CVD–SiC film in two-dimension is simulated with Potts Monte Carlo method. The relationship between the microstructure morphology and growth rate, nucleating density is analyzed. The simulation result is given as the following. Both competitive growth and coarsening effect have been found in the growth process. The increase of nucleation density results in thinning of the grain size in SiC film. The grain size distribution is found to be self-similar, not differed with the corresponding growth parameter. The fitted result of Weibull and Louat function is better than that of lognormal function obviously. The result is in agreement with the corresponding theory and experiment conclusion well.},\n\tnumber = {4},\n\turldate = {2023-10-30},\n\tjournal = {Computational Materials Science},\n\tauthor = {Liu, Cui-Xia and Yang, Yan-Qing and Zhang, Rong-Jun and Luo, Xian},\n\tmonth = feb,\n\tyear = {2009},\n\tkeywords = {Chemical vapor deposition, Grain growth, Monte Carlo, SiC Film},\n\tpages = {1281--1285},\n}\n\n\n\n\n\n\n\n
\n
\n\n\n
\n In analyzing microstructure evolution of material, study for the process of grain growth is both theoretically and practically significant. On (111) and (110) facets, the process of CVD–SiC film in two-dimension is simulated with Potts Monte Carlo method. The relationship between the microstructure morphology and growth rate, nucleating density is analyzed. The simulation result is given as the following. Both competitive growth and coarsening effect have been found in the growth process. The increase of nucleation density results in thinning of the grain size in SiC film. The grain size distribution is found to be self-similar, not differed with the corresponding growth parameter. The fitted result of Weibull and Louat function is better than that of lognormal function obviously. The result is in agreement with the corresponding theory and experiment conclusion well.\n
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\n \n\n \n \n Si-Zhou, J.; Xiang, X.; Zhao-Ke, C.; Peng, X.; and Bai-Yun, H.\n\n\n \n \n \n \n Influence factors of C/C–SiC dual matrix composites prepared by reactive melt infiltration.\n \n \n \n\n\n \n\n\n\n Materials & Design, 30(9): 3738–3742. October 2009.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{si-zhou_influence_2009,\n\ttitle = {Influence factors of {C}/{C}–{SiC} dual matrix composites prepared by reactive melt infiltration},\n\tvolume = {30},\n\tissn = {0261-3069},\n\tdoi = {10.1016/j.matdes.2009.02.013},\n\tabstract = {The effects of the type of carbon matrix, the infiltration temperature and high temperature treatment (HTT) on the infiltration behavior of molten Si and preparation of C/C–SiC dual matrix composites have been investigated. The results showed that: Resin carbon matrix is benificial to the infiltration of molten Si than pyrolysis carbon matrix. 1650°C is more suitable for the infiltration of molten Si in porous C/C preforms than 1550°C. The high infiltration depth at 1650°C is responsible for the high density of C/C–SiC composites. HTT facilitates to the infiltration of molten Si and the formation of more SiC. High density and low open porosity C/C–SiC dual matrix composites can be prepared by optimal reactive molten infiltration method. The flexural strength, elastic modul and impact toughness of C/C–SiC composites are high up to 265.4MPa, 28.1GPa and 28.5kJ/m2 respectively. Heat treatment at 2300°C decreases the composites flexural strength, elastic modul and impact toughness, but improve the fracture behavior of C/C–SiC dual matrix composites.},\n\tnumber = {9},\n\turldate = {2023-10-30},\n\tjournal = {Materials \\& Design},\n\tauthor = {Si-Zhou, Jiang and Xiang, Xiong and Zhao-Ke, Chen and Peng, Xiao and Bai-Yun, Huang},\n\tmonth = oct,\n\tyear = {2009},\n\tkeywords = {A. Ceramic matrix composites, B. Fabrics, E. Mechanical},\n\tpages = {3738--3742},\n}\n\n\n\n
\n
\n\n\n
\n The effects of the type of carbon matrix, the infiltration temperature and high temperature treatment (HTT) on the infiltration behavior of molten Si and preparation of C/C–SiC dual matrix composites have been investigated. The results showed that: Resin carbon matrix is benificial to the infiltration of molten Si than pyrolysis carbon matrix. 1650°C is more suitable for the infiltration of molten Si in porous C/C preforms than 1550°C. The high infiltration depth at 1650°C is responsible for the high density of C/C–SiC composites. HTT facilitates to the infiltration of molten Si and the formation of more SiC. High density and low open porosity C/C–SiC dual matrix composites can be prepared by optimal reactive molten infiltration method. The flexural strength, elastic modul and impact toughness of C/C–SiC composites are high up to 265.4MPa, 28.1GPa and 28.5kJ/m2 respectively. Heat treatment at 2300°C decreases the composites flexural strength, elastic modul and impact toughness, but improve the fracture behavior of C/C–SiC dual matrix composites.\n
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\n \n\n \n \n Hurtado, S.; Cabrera, N. L.; Lin, M. H.; Arellano, L.; and Espinosa, L. L.\n\n\n \n \n \n \n Diversifying Science: Underrepresented Student Experiences in Structured Research Programs.\n \n \n \n\n\n \n\n\n\n Research in Higher Education, 50(2): 189–214. March 2009.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{hurtado2009,\n\ttitle = {Diversifying {Science}: {Underrepresented} {Student} {Experiences} in {Structured} {Research} {Programs}},\n\tvolume = {50},\n\tissn = {1573-188X},\n\tshorttitle = {Diversifying {Science}},\n\tdoi = {10.1007/s11162-008-9114-7},\n\tabstract = {Targeting four institutions with structured science research programs for undergraduates, this study focuses on how underrepresented students experience science. Several key themes emerged from focus group discussions: learning to become research scientists, experiences with the culture of science, and views on racial and social stigma. Participants spoke of essential factors for becoming a scientist, but their experiences also raised complex issues about the role of race and social stigma in scientific training. Students experienced the collaborative and empowering culture of science, exhibited strong science identities and high self-efficacy, while developing directed career goals as a result of “doing science” in these programs.},\n\tlanguage = {en},\n\tnumber = {2},\n\turldate = {2023-09-08},\n\tjournal = {Research in Higher Education},\n\tauthor = {Hurtado, Sylvia and Cabrera, Nolan L. and Lin, Monica H. and Arellano, Lucy and Espinosa, Lorelle L.},\n\tmonth = mar,\n\tyear = {2009},\n\tkeywords = {Identity, Racial/ethnic minorities, Self-efficacy, Stigma, Undergraduate science research},\n\tpages = {189--214},\n}\n\n\n\n\n\n\n\n
\n
\n\n\n
\n Targeting four institutions with structured science research programs for undergraduates, this study focuses on how underrepresented students experience science. Several key themes emerged from focus group discussions: learning to become research scientists, experiences with the culture of science, and views on racial and social stigma. Participants spoke of essential factors for becoming a scientist, but their experiences also raised complex issues about the role of race and social stigma in scientific training. Students experienced the collaborative and empowering culture of science, exhibited strong science identities and high self-efficacy, while developing directed career goals as a result of “doing science” in these programs.\n
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\n \n\n \n \n Candler, G.; and Nompelis, I.\n\n\n \n \n \n \n \n Computational Fluid Dynamics for Atmospheric Entry.\n \n \n \n \n\n\n \n\n\n\n Technical Report ADA568031, 2009.\n Section: Technical Reports\n\n\n\n
\n\n\n\n \n \n \"ComputationalPaper\n  \n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@techreport{candler2009,\n\ttitle = {Computational {Fluid} {Dynamics} for {Atmospheric} {Entry}},\n\turl = {https://apps.dtic.mil/sti/citations/ADA568031},\n\tabstract = {These notes are arranged in the following manner. In the introduction section, we use several examples to illustrate some of the issues that must be addressed when we model hypersonic flows. This leads to a discussion of what types of computational fluid dynamics methods are suitable for these flows. Then the conservation equations for a mixture of chemically reacting and weakly ionized gases is developed. We discuss the thermochemistry models and the relevant boundary conditions for these flows. Then in the third section, computational fluid dynamics methods for these flows are discussed. We analyze the conservation equations, and discuss an upwind method. Then, the integration of the source terms is discussed. In the fourth section we discuss several advanced topics in the modeling of hypersonic flows.},\n\tlanguage = {en},\n\tnumber = {ADA568031},\n\turldate = {2023-08-17},\n\tauthor = {Candler, Graham and Nompelis, Ioannis},\n\tyear = {2009},\n\tnote = {Section: Technical Reports},\n}\n\n\n\n\n\n\n\n
\n
\n\n\n
\n These notes are arranged in the following manner. In the introduction section, we use several examples to illustrate some of the issues that must be addressed when we model hypersonic flows. This leads to a discussion of what types of computational fluid dynamics methods are suitable for these flows. Then the conservation equations for a mixture of chemically reacting and weakly ionized gases is developed. We discuss the thermochemistry models and the relevant boundary conditions for these flows. Then in the third section, computational fluid dynamics methods for these flows are discussed. We analyze the conservation equations, and discuss an upwind method. Then, the integration of the source terms is discussed. In the fourth section we discuss several advanced topics in the modeling of hypersonic flows.\n
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\n \n\n \n \n Zhang, W.; Ye, Z.; Zhang, C.; and Liu, F.\n\n\n \n \n \n \n Supersonic Flutter Analysis Based on a Local Piston Theory.\n \n \n \n\n\n \n\n\n\n AIAA Journal, 47(10). 2009.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{zhang2009,\n\ttitle = {Supersonic {Flutter} {Analysis} {Based} on a {Local} {Piston} {Theory}},\n\tvolume = {47},\n\tdoi = {10.2514/1.37750},\n\tabstract = {A highly efficient local-piston theory is presented for the prediction of inviscid unsteady pressure loads at supersonic and hypersonic speeds. A steady mean flow solution is first obtained by an Euler method. The classical piston theory is modified to apply locally at each point on the airfoil surface on top of the local mean flow to obtain the unsteady pressure perturbations caused by the deviation of the airfoil surface from its mean location without the need of performing unsteady Euler computations. Results of two-and three-dimensional unsteady air loads and flutter predictions are compared with those obtained by the classical piston theory and an unsteady Euler method to assess the accuracy and validity range in airfoil thickness, flight Mach number, and angle of attack and with the presence of blunt leading edges. The local-piston theory is found to offer superior accuracy and much wider validity range compared with the classical piston theory, with the cost of only a fraction of the computational time needed by an unsteady Euler method. Nomenclature A = aerodynamic stiffness matrix a = speed of sound B = aerodynamic damping matrix b = airfoil semichord C l = lift coefficient C m = moment coefficient C p = pressure coefficient h = plunge displacement at the elastic axis, positive down I = cross-sectional mass moment of inertia about its elastic axis K h , K = airfoil plunge stiffness, airfoil pitch stiffness k = reduced frequency, ! b=V 1 M = Mach number m = airfoil mass per unit span p = pressure r = dimensionless radius of gyration about elastic axis S = static moment per unit span t = physical time x = dimensionless static imbalance of the airfoil about its elastic axis V f = reduced flutter speed V 1 = freestream speed = angle of attack, torsion deflection 0 = airfoil steady (mean) background flow angle of attack = amplitude of the pitch motion = mass ratio, m=b 2 = air density = dimensionless time, ! t ! = circular frequency, rad=s ! , ! h = uncoupled frequency of plunging and pitching},\n\tnumber = {10},\n\tjournal = {AIAA Journal},\n\tauthor = {Zhang, Wei-Wei and Ye, Zheng-Yin and Zhang, Chen-An and Liu, Feng},\n\tyear = {2009},\n}\n\n\n\n
\n
\n\n\n
\n A highly efficient local-piston theory is presented for the prediction of inviscid unsteady pressure loads at supersonic and hypersonic speeds. A steady mean flow solution is first obtained by an Euler method. The classical piston theory is modified to apply locally at each point on the airfoil surface on top of the local mean flow to obtain the unsteady pressure perturbations caused by the deviation of the airfoil surface from its mean location without the need of performing unsteady Euler computations. Results of two-and three-dimensional unsteady air loads and flutter predictions are compared with those obtained by the classical piston theory and an unsteady Euler method to assess the accuracy and validity range in airfoil thickness, flight Mach number, and angle of attack and with the presence of blunt leading edges. The local-piston theory is found to offer superior accuracy and much wider validity range compared with the classical piston theory, with the cost of only a fraction of the computational time needed by an unsteady Euler method. Nomenclature A = aerodynamic stiffness matrix a = speed of sound B = aerodynamic damping matrix b = airfoil semichord C l = lift coefficient C m = moment coefficient C p = pressure coefficient h = plunge displacement at the elastic axis, positive down I = cross-sectional mass moment of inertia about its elastic axis K h , K = airfoil plunge stiffness, airfoil pitch stiffness k = reduced frequency, ! b=V 1 M = Mach number m = airfoil mass per unit span p = pressure r = dimensionless radius of gyration about elastic axis S = static moment per unit span t = physical time x = dimensionless static imbalance of the airfoil about its elastic axis V f = reduced flutter speed V 1 = freestream speed = angle of attack, torsion deflection 0 = airfoil steady (mean) background flow angle of attack = amplitude of the pitch motion = mass ratio, m=b 2 = air density = dimensionless time, ! t ! = circular frequency, rad=s ! , ! h = uncoupled frequency of plunging and pitching\n
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\n \n\n \n \n Jones, C.\n\n\n \n \n \n \n Recommendations From the Workshop on Communications Through Plasma During Hypersonic Flight.\n \n \n \n\n\n \n\n\n\n In Alberquerque, New Mexico, February 2009. AIAA 2009-1718\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{jones2009,\n\taddress = {Alberquerque, New Mexico},\n\ttitle = {Recommendations {From} the {Workshop} on {Communications} {Through} {Plasma} {During} {Hypersonic} {Flight}},\n\tdoi = {10.2514/6.2009-1718},\n\tpublisher = {AIAA 2009-1718},\n\tauthor = {Jones, Charles},\n\tmonth = feb,\n\tyear = {2009},\n}\n\n\n\n
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\n \n\n \n \n Jones, C. H.\n\n\n \n \n \n \n \n Recommendations from the workshop on communications through plasma during hypersonic flight.\n \n \n \n \n\n\n \n\n\n\n In U.S. Air Force T and E Days 2009, 2009. American Institute of Aeronautics and Astronautics Inc.\n \n\n\n\n
\n\n\n\n \n \n \"RecommendationsPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{jones2009b,\n\ttitle = {Recommendations from the workshop on communications through plasma during hypersonic flight},\n\tisbn = {978-1-56347-970-0},\n\turl = {http://arc.aiaa.org},\n\tdoi = {10.2514/6.2009-1718},\n\turldate = {2021-05-31},\n\tbooktitle = {U.{S}. {Air} {Force} {T} and {E} {Days} 2009},\n\tpublisher = {American Institute of Aeronautics and Astronautics Inc.},\n\tauthor = {Jones, Charles H.},\n\tyear = {2009},\n}\n\n\n\n
\n
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\n \n\n \n \n Jones, C. H.\n\n\n \n \n \n \n \n Recommendations from the workshop on communications through plasma during hypersonic flight.\n \n \n \n \n\n\n \n\n\n\n In 2009. American Institute of Aeronautics and Astronautics Inc.\n \n\n\n\n
\n\n\n\n \n \n \"RecommendationsPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{jones2009a,\n\ttitle = {Recommendations from the workshop on communications through plasma during hypersonic flight},\n\tisbn = {978-1-56347-970-0},\n\turl = {http://arc.aiaa.org},\n\tdoi = {10.2514/6.2009-1718},\n\tpublisher = {American Institute of Aeronautics and Astronautics Inc.},\n\tauthor = {Jones, Charles H.},\n\tyear = {2009},\n}\n\n\n\n
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\n \n\n \n \n Bisek, N. J; Boyd, I. D; and Poggie, J.\n\n\n \n \n \n \n Numerical Study of Plasma-Assisted Aerodynamic Control for Hypersonic Vehicles.\n \n \n \n\n\n \n\n\n\n Journal of Spacecraft and Rockets, 46(3): 568–576. 2009.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{bisek2009,\n\ttitle = {Numerical {Study} of {Plasma}-{Assisted} {Aerodynamic} {Control} for {Hypersonic} {Vehicles}},\n\tvolume = {46},\n\tnumber = {3},\n\tjournal = {Journal of Spacecraft and Rockets},\n\tauthor = {Bisek, Nicholas J and Boyd, Iain D and Poggie, Jonathan},\n\tyear = {2009},\n\tpages = {568--576},\n}\n\n\n\n
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\n \n\n \n \n Martin, A.; and Boyd, I. D\n\n\n \n \n \n \n \n Implicit implementation of material response and moving meshes for hypersonic re-entry ablation.\n \n \n \n \n\n\n \n\n\n\n In 2009. AIAA 2009-670\n \n\n\n\n
\n\n\n\n \n \n \"ImplicitPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{martin2009,\n\ttitle = {Implicit implementation of material response and moving meshes for hypersonic re-entry ablation},\n\turl = {http://arc.aiaa.org},\n\tdoi = {10.2514/6.2009-670},\n\tpublisher = {AIAA 2009-670},\n\tauthor = {Martin, Alexandre and Boyd, Iain D},\n\tyear = {2009},\n}\n\n\n\n
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\n \n\n \n \n Wyckham, C. M; and Smits, A. J\n\n\n \n \n \n \n \n Aero-Optic Distortion in Transonic and Hypersonic Turbulent Boundary Layers.\n \n \n \n \n\n\n \n\n\n\n AIAA Journal, 47(9). 2009.\n \n\n\n\n
\n\n\n\n \n \n \"Aero-OpticPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{wyckham2009a,\n\ttitle = {Aero-{Optic} {Distortion} in {Transonic} and {Hypersonic} {Turbulent} {Boundary} {Layers}},\n\tvolume = {47},\n\turl = {http://arc.aiaa.org},\n\tdoi = {10.2514/1.41453},\n\tabstract = {A two-dimensional Shack-Hartmann wave-front sensor is used to study aero-optic distortion in turbulent boundary layers at transonic and hypersonic speeds, with and without gas injection. The large-scale motions in the outer layer, of the order of the boundary-layer thickness in size, are shown to dominate the aero-optic distortion. Gas injection always reduced the Strehl ratio, with helium injection generally giving lower Strehl ratios than nitrogen injection. The large aperture approximation is shown to be accurate for a wide variety of aberrations regardless of Mach number and gas injection. A new scaling argument for the root-mean-square phase distortion is proposed that appears to collapse the data better than previous models. Nomenclature C B = constant defined by Eq. (20), OPD rms K GD e M 2 e u 0 rms =U e † rms C f = skin friction coefficient C w = constant defined by Eq. (16), OPD rms r 3=2 2 K GD e M 2 e  C f p I = intensity K GD = Galdstone-Dale constant M = Mach number n = index of refraction p = pressure Re = Reynolds number based on freestream values and r = recovery factor r 1 = U i =U e r 2 = T i =T e r 3 = constant defined by Eq. (14),  u 02 w q † 0:5 =  u 02 w q † i T = temperature t = time U = velocity in the streamwise direction x = streamwise distance y = wall-normal distance from the flat plate model z = spanwise distance = ratio of specific heats = 99\\% boundary-layer thickness = displacement thickness = momentum thickness = integral length scale = wavelength of light = kinematic viscosity = density SL = sea level density in a standard atmosphere = shear stress Subscripts e = freestream value i = intermediate value rms = root mean square value w = value at the wall 0 = maximum value Superscripts † = mean value 0 = fluctuation from the mean},\n\tnumber = {9},\n\tjournal = {AIAA Journal},\n\tauthor = {Wyckham, Christopher M and Smits, Alexander J},\n\tyear = {2009},\n}\n\n\n\n
\n
\n\n\n
\n A two-dimensional Shack-Hartmann wave-front sensor is used to study aero-optic distortion in turbulent boundary layers at transonic and hypersonic speeds, with and without gas injection. The large-scale motions in the outer layer, of the order of the boundary-layer thickness in size, are shown to dominate the aero-optic distortion. Gas injection always reduced the Strehl ratio, with helium injection generally giving lower Strehl ratios than nitrogen injection. The large aperture approximation is shown to be accurate for a wide variety of aberrations regardless of Mach number and gas injection. A new scaling argument for the root-mean-square phase distortion is proposed that appears to collapse the data better than previous models. Nomenclature C B = constant defined by Eq. (20), OPD rms K GD e M 2 e u 0 rms =U e † rms C f = skin friction coefficient C w = constant defined by Eq. (16), OPD rms r 3=2 2 K GD e M 2 e  C f p I = intensity K GD = Galdstone-Dale constant M = Mach number n = index of refraction p = pressure Re = Reynolds number based on freestream values and r = recovery factor r 1 = U i =U e r 2 = T i =T e r 3 = constant defined by Eq. (14),  u 02 w q † 0:5 =  u 02 w q † i T = temperature t = time U = velocity in the streamwise direction x = streamwise distance y = wall-normal distance from the flat plate model z = spanwise distance = ratio of specific heats = 99% boundary-layer thickness = displacement thickness = momentum thickness = integral length scale = wavelength of light = kinematic viscosity = density SL = sea level density in a standard atmosphere = shear stress Subscripts e = freestream value i = intermediate value rms = root mean square value w = value at the wall 0 = maximum value Superscripts † = mean value 0 = fluctuation from the mean\n
\n\n\n
\n\n\n
\n \n\n \n \n Wyckham, C. M; and Smits, A. J\n\n\n \n \n \n \n Aero-Optic Distortion in Transonic and Hypersonic Turbulent Boundary Layers.\n \n \n \n\n\n \n\n\n\n AIAA Journal, 47(9): 2158–2168. September 2009.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{wyckham2009b,\n\ttitle = {Aero-{Optic} {Distortion} in {Transonic} and {Hypersonic} {Turbulent} {Boundary} {Layers}},\n\tvolume = {47},\n\tnumber = {9},\n\tjournal = {AIAA Journal},\n\tauthor = {Wyckham, Christopher M and Smits, Alexander J},\n\tmonth = sep,\n\tyear = {2009},\n\tpages = {2158--2168},\n}\n\n\n\n
\n
\n\n\n\n
\n\n\n
\n \n\n \n \n Wyckham, C. M; and Smits, A. J\n\n\n \n \n \n \n Aero-Optic Distortion in Transonic and Hypersonic Turbulent Boundary Layers.\n \n \n \n\n\n \n\n\n\n AIAA Journal, 47(9). 2009.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{wyckham2009,\n\ttitle = {Aero-{Optic} {Distortion} in {Transonic} and {Hypersonic} {Turbulent} {Boundary} {Layers}},\n\tvolume = {47},\n\tdoi = {10.2514/1.41453},\n\tabstract = {A two-dimensional Shack-Hartmann wave-front sensor is used to study aero-optic distortion in turbulent boundary layers at transonic and hypersonic speeds, with and without gas injection. The large-scale motions in the outer layer, of the order of the boundary-layer thickness in size, are shown to dominate the aero-optic distortion. Gas injection always reduced the Strehl ratio, with helium injection generally giving lower Strehl ratios than nitrogen injection. The large aperture approximation is shown to be accurate for a wide variety of aberrations regardless of Mach number and gas injection. A new scaling argument for the root-mean-square phase distortion is proposed that appears to collapse the data better than previous models. Nomenclature C B = constant defined by Eq. (20), OPD rms K GD e M 2 e u 0 rms =U e † rms C f = skin friction coefficient C w = constant defined by Eq. (16), OPD rms r 3=2 2 K GD e M 2 e  C f p I = intensity K GD = Galdstone-Dale constant M = Mach number n = index of refraction p = pressure Re = Reynolds number based on freestream values and r = recovery factor r 1 = U i =U e r 2 = T i =T e r 3 = constant defined by Eq. (14),  u 02 w q † 0:5 =  u 02 w q † i T = temperature t = time U = velocity in the streamwise direction x = streamwise distance y = wall-normal distance from the flat plate model z = spanwise distance = ratio of specific heats = 99\\% boundary-layer thickness = displacement thickness = momentum thickness = integral length scale = wavelength of light = kinematic viscosity = density SL = sea level density in a standard atmosphere = shear stress Subscripts e = freestream value i = intermediate value rms = root mean square value w = value at the wall 0 = maximum value Superscripts † = mean value 0 = fluctuation from the mean},\n\tnumber = {9},\n\turldate = {2021-07-11},\n\tjournal = {AIAA Journal},\n\tauthor = {Wyckham, Christopher M and Smits, Alexander J},\n\tyear = {2009},\n}\n\n\n\n
\n
\n\n\n
\n A two-dimensional Shack-Hartmann wave-front sensor is used to study aero-optic distortion in turbulent boundary layers at transonic and hypersonic speeds, with and without gas injection. The large-scale motions in the outer layer, of the order of the boundary-layer thickness in size, are shown to dominate the aero-optic distortion. Gas injection always reduced the Strehl ratio, with helium injection generally giving lower Strehl ratios than nitrogen injection. The large aperture approximation is shown to be accurate for a wide variety of aberrations regardless of Mach number and gas injection. A new scaling argument for the root-mean-square phase distortion is proposed that appears to collapse the data better than previous models. Nomenclature C B = constant defined by Eq. (20), OPD rms K GD e M 2 e u 0 rms =U e † rms C f = skin friction coefficient C w = constant defined by Eq. (16), OPD rms r 3=2 2 K GD e M 2 e  C f p I = intensity K GD = Galdstone-Dale constant M = Mach number n = index of refraction p = pressure Re = Reynolds number based on freestream values and r = recovery factor r 1 = U i =U e r 2 = T i =T e r 3 = constant defined by Eq. (14),  u 02 w q † 0:5 =  u 02 w q † i T = temperature t = time U = velocity in the streamwise direction x = streamwise distance y = wall-normal distance from the flat plate model z = spanwise distance = ratio of specific heats = 99% boundary-layer thickness = displacement thickness = momentum thickness = integral length scale = wavelength of light = kinematic viscosity = density SL = sea level density in a standard atmosphere = shear stress Subscripts e = freestream value i = intermediate value rms = root mean square value w = value at the wall 0 = maximum value Superscripts † = mean value 0 = fluctuation from the mean\n
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\n \n\n \n \n Valentini, P.; Schwartzentruber, T. E.; and Cozmuta, I.\n\n\n \n \n \n \n \n A mechanism-based finite-rate surface catalysis model for simulating reacting flows.\n \n \n \n \n\n\n \n\n\n\n In 2009. American Institute of Aeronautics and Astronautics Inc.\n \n\n\n\n
\n\n\n\n \n \n \"APaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{valentini2009,\n\ttitle = {A mechanism-based finite-rate surface catalysis model for simulating reacting flows},\n\tisbn = {978-1-56347-975-5},\n\turl = {https://arc.aiaa.org/doi/10.2514/6.2009-3935},\n\tdoi = {10.2514/6.2009-3935},\n\tabstract = {A mechanism-based finite-rate wall boundary condition is implemented in a state-of-the- art finite volume CFD thermochemical nonequilibrium code to study a high enthalpy CO2 flow over blunt bodies. All the relevant surface processes responsible for the catalytic behavior of the wall are accounted for, including adsorption and desorption (both atomic and molecular), and Eley-Rideal and Langmuir-Hinshelwood recombinations. The model only requires the specification of the reaction rates for each of the processes considered, and the law of mass action is used to compute surface coverages and mass fluxes produced or consumed at the wall due to its catalytic activity. The kinetic rates are chosen to describe a platinum surface, with a fairly high degree of catalycity with respect to CO oxidation. As expected, the predicted heat flux is intermediate between the two extrema, namely the non-catalytic and supercatalytic wall assumptions. Because the only input of the model are the reaction rates, which are usually unavailable or affected by a large experimental uncertainty, the use of Molecular Dynamics simulations employing the Quantum Chemistry based reactive force field ReaxFF is proposed as a novel approach to both determine and characterize each of the underlying processes which collectively cause the wall catalytic activity. Because (dissociative) adsorption is a fundamental step leading to surface recombinations, the sticking of O2 on Pt(111) is studied using ReaxFF Molecular Dynamics simulations. Copyright © 2009 by Paolo Valentini, Thomas E. Schwartzentruber, and Ioana Cozmuta.},\n\tpublisher = {American Institute of Aeronautics and Astronautics Inc.},\n\tauthor = {Valentini, Paolo and Schwartzentruber, Thomas E. and Cozmuta, Ioana},\n\tyear = {2009},\n}\n\n\n\n
\n
\n\n\n
\n A mechanism-based finite-rate wall boundary condition is implemented in a state-of-the- art finite volume CFD thermochemical nonequilibrium code to study a high enthalpy CO2 flow over blunt bodies. All the relevant surface processes responsible for the catalytic behavior of the wall are accounted for, including adsorption and desorption (both atomic and molecular), and Eley-Rideal and Langmuir-Hinshelwood recombinations. The model only requires the specification of the reaction rates for each of the processes considered, and the law of mass action is used to compute surface coverages and mass fluxes produced or consumed at the wall due to its catalytic activity. The kinetic rates are chosen to describe a platinum surface, with a fairly high degree of catalycity with respect to CO oxidation. As expected, the predicted heat flux is intermediate between the two extrema, namely the non-catalytic and supercatalytic wall assumptions. Because the only input of the model are the reaction rates, which are usually unavailable or affected by a large experimental uncertainty, the use of Molecular Dynamics simulations employing the Quantum Chemistry based reactive force field ReaxFF is proposed as a novel approach to both determine and characterize each of the underlying processes which collectively cause the wall catalytic activity. Because (dissociative) adsorption is a fundamental step leading to surface recombinations, the sticking of O2 on Pt(111) is studied using ReaxFF Molecular Dynamics simulations. Copyright © 2009 by Paolo Valentini, Thomas E. Schwartzentruber, and Ioana Cozmuta.\n
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\n  \n 2008\n \n \n (14)\n \n \n
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\n \n\n \n \n Najm, H.\n\n\n \n \n \n \n Uncertainty Quantification and Polynomial Chaos Techniques in Computational Fluid Dynamics.\n \n \n \n\n\n \n\n\n\n Annual Review of Fluid Mechanics. June 2008.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{najm2008,\n\ttitle = {Uncertainty {Quantification}\nand {Polynomial} {Chaos}\nTechniques in {Computational}\nFluid {Dynamics}},\n\tdoi = {10.1146/annurev.fluid.010908.165248},\n\tjournal = {Annual Review of Fluid Mechanics},\n\tauthor = {Najm, Habib},\n\tmonth = jun,\n\tyear = {2008},\n}\n\n\n\n
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\n \n\n \n \n Bonet, J.; and Wood, R. D.\n\n\n \n \n \n \n Nonlinear Continuum Mechanics for Finite Element Analysis.\n \n \n \n\n\n \n\n\n\n Cambridge University Press, Cambridge, 2 edition, 2008.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@book{bonet2008,\n\taddress = {Cambridge},\n\tedition = {2},\n\ttitle = {Nonlinear {Continuum} {Mechanics} for {Finite} {Element} {Analysis}},\n\tabstract = {Designing engineering components that make optimal use of materials requires consideration of the nonlinear characteristics associated with both manufacturing and working environments. The modeling of these characteristics can only be done through numerical formulation and simulation, and this requires an understanding of both the theoretical background and associated computer solution techniques. By presenting both nonlinear continuum analysis and associated finite element techniques under one roof, Bonet and Wood provide, in this edition of this successful text, a complete, clear, and unified treatment of these important subjects. New chapters dealing with hyperelastic plastic behavior are included, and the authors have thoroughly updated the FLagSHyP program, freely accessible at www.flagshyp.com. Worked examples and exercises complete each chapter, making the text an essential resource for postgraduates studying nonlinear continuum mechanics. It is also ideal for those in industry requiring an appreciation of the way in which their computer simulation programs work.},\n\turldate = {2024-06-12},\n\tpublisher = {Cambridge University Press},\n\tauthor = {Bonet, Javier and Wood, Richard D.},\n\tyear = {2008},\n\tdoi = {10.1017/CBO9780511755446},\n}\n\n\n\n\n\n\n\n
\n
\n\n\n
\n Designing engineering components that make optimal use of materials requires consideration of the nonlinear characteristics associated with both manufacturing and working environments. The modeling of these characteristics can only be done through numerical formulation and simulation, and this requires an understanding of both the theoretical background and associated computer solution techniques. By presenting both nonlinear continuum analysis and associated finite element techniques under one roof, Bonet and Wood provide, in this edition of this successful text, a complete, clear, and unified treatment of these important subjects. New chapters dealing with hyperelastic plastic behavior are included, and the authors have thoroughly updated the FLagSHyP program, freely accessible at www.flagshyp.com. Worked examples and exercises complete each chapter, making the text an essential resource for postgraduates studying nonlinear continuum mechanics. It is also ideal for those in industry requiring an appreciation of the way in which their computer simulation programs work.\n
\n\n\n
\n\n\n
\n \n\n \n \n Jiang, G.; Yang, J.; Xu, Y.; Gao, J.; Zhang, J.; Zhang, L.; Cheng, L.; and Lou, J.\n\n\n \n \n \n \n Effect of graphitization on microstructure and tribological properties of C/SiC composites prepared by reactive melt infiltration.\n \n \n \n\n\n \n\n\n\n Composites Science and Technology, 68(12): 2468–2473. September 2008.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{jiang_effect_2008,\n\tseries = {Deformation and {Fracture} of {Composites}: {Analytical}, {Numerical} and {Experimental} {Techniques}, with regular papers},\n\ttitle = {Effect of graphitization on microstructure and tribological properties of {C}/{SiC} composites prepared by reactive melt infiltration},\n\tvolume = {68},\n\tissn = {0266-3538},\n\tdoi = {10.1016/j.compscitech.2008.04.025},\n\tabstract = {Carbon fiber reinforced SiC matrix (C/SiC) composites for use in future advanced braking systems were prepared by reactive melt infiltration with and without graphitization before siliconizing. The effect of graphitization on tribological properties of C/SiC composites was studied by simulating the normal landing of aircraft. The results showed that a dense microstructure and high thermal diffusivity were obtained by the graphitization. After braking tests, high and stable coefficient of friction could be obtained, due to the formation of uniform and continuous debris film on the rubbing surface of the graphitized samples. Simultaneously, the wear rate was slightly higher because of the high coefficient of friction, but still lower than the results in other researches.},\n\tnumber = {12},\n\turldate = {2023-10-30},\n\tjournal = {Composites Science and Technology},\n\tauthor = {Jiang, Guangpeng and Yang, Jianfeng and Xu, Yongdong and Gao, Jiqiang and Zhang, Junzhan and Zhang, Litong and Cheng, Laifei and Lou, Jianjun},\n\tmonth = sep,\n\tyear = {2008},\n\tkeywords = {A. Ceramic–matrix composites, B. Friction/wear, E. Graphitization, E. Liquid metal infiltration},\n\tpages = {2468--2473},\n}\n\n\n\n
\n
\n\n\n
\n Carbon fiber reinforced SiC matrix (C/SiC) composites for use in future advanced braking systems were prepared by reactive melt infiltration with and without graphitization before siliconizing. The effect of graphitization on tribological properties of C/SiC composites was studied by simulating the normal landing of aircraft. The results showed that a dense microstructure and high thermal diffusivity were obtained by the graphitization. After braking tests, high and stable coefficient of friction could be obtained, due to the formation of uniform and continuous debris film on the rubbing surface of the graphitized samples. Simultaneously, the wear rate was slightly higher because of the high coefficient of friction, but still lower than the results in other researches.\n
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\n \n\n \n \n Gidzak, V.; Barnhardt, M.; Drayna, T.; Nompelis, I.; Candler, G. V; and Garrard, W.\n\n\n \n \n \n \n Simulation of Fluid-Structure Interaction of the Mars Science Laboratory Parachute.\n \n \n \n\n\n \n\n\n\n In Honolulu, HI, 2008. \\AIAA Paper\\ 2008-6910\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{gidzak2008,\n\taddress = {Honolulu, HI},\n\ttitle = {Simulation of {Fluid}-{Structure} {Interaction} of the {Mars} {Science} {Laboratory} {Parachute}},\n\tpublisher = {\\{AIAA Paper\\} 2008-6910},\n\tauthor = {Gidzak, Vladimyr and Barnhardt, Michael and Drayna, Travis and Nompelis, Ioannis and Candler, Graham V and Garrard, William},\n\tyear = {2008},\n}\n\n\n\n
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\n \n\n \n \n Martin, A.; and Boyd, I. D.\n\n\n \n \n \n \n \n Simulation of pyrolysis gas within a thermal protection system.\n \n \n \n \n\n\n \n\n\n\n In 2008. AIAA 2008-3805\n \n\n\n\n
\n\n\n\n \n \n \"SimulationPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{martin2008,\n\ttitle = {Simulation of pyrolysis gas within a thermal protection system},\n\turl = {https://arc.aiaa.org/doi/abs/10.2514/6.2008-3805},\n\tdoi = {10.2514/6.2008-3805},\n\tabstract = {As the first part of an ongoing study on heat flux and abation on hypersonic vehicles, a material response implicit solver with solid ablation and pyrolysis is developed. As a first step, code-to-code validations and comparisons with experimental data are performed. A study of the various effects of pyrolysis gas within an ablator is also performed; using realistic re-entry conditions on a generic carbon-phenolic ablator, conditions for non-Darcian behavior are modeled, suggesting the use of Forchheimer's Law to calculate gas velocity. The necessary conditions required for kinetic energy to be relevant are also highlighted. The code is then coupled to LeMANS, a CFD solver for the simulation of weakly ionized hypersonic flows in thermo-chemical non-equilibrium developed at The University of Michigan. A summary of the coupling validation is presented. All results show good agreement with published numerical results or analytical solutions. Copyright © 2008 by the American Institute of Aeronautics and Astronautics, Inc.},\n\tpublisher = {AIAA 2008-3805},\n\tauthor = {Martin, Alexandre and Boyd, Iain D.},\n\tyear = {2008},\n}\n\n\n\n
\n
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\n As the first part of an ongoing study on heat flux and abation on hypersonic vehicles, a material response implicit solver with solid ablation and pyrolysis is developed. As a first step, code-to-code validations and comparisons with experimental data are performed. A study of the various effects of pyrolysis gas within an ablator is also performed; using realistic re-entry conditions on a generic carbon-phenolic ablator, conditions for non-Darcian behavior are modeled, suggesting the use of Forchheimer's Law to calculate gas velocity. The necessary conditions required for kinetic energy to be relevant are also highlighted. The code is then coupled to LeMANS, a CFD solver for the simulation of weakly ionized hypersonic flows in thermo-chemical non-equilibrium developed at The University of Michigan. A summary of the coupling validation is presented. All results show good agreement with published numerical results or analytical solutions. Copyright © 2008 by the American Institute of Aeronautics and Astronautics, Inc.\n
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\n \n\n \n \n Ali Mani Meng Wang, P. M.\n\n\n \n \n \n \n Resolution requirements for aero-optical simulations.\n \n \n \n\n\n \n\n\n\n Journal of Computational Physics, 227(21): 9008–9020. February 2008.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{alimanimengwang2008,\n\ttitle = {Resolution requirements for aero-optical simulations},\n\tvolume = {227},\n\tnumber = {21},\n\tjournal = {Journal of Computational Physics},\n\tauthor = {Ali Mani Meng Wang, Parviz Moin},\n\tmonth = feb,\n\tyear = {2008},\n\tpages = {9008--9020},\n}\n\n\n\n
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\n \n\n \n \n Bisek, N J; Boyd, I D; and Poggie, J\n\n\n \n \n \n \n Numerical Study of Energy Deposition Requirements for Aerodynamic Control of Hypersonic Vehicles.\n \n \n \n\n\n \n\n\n\n In January 2008. \\AIAA Paper\\ 2008-1109\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{bisek2008,\n\ttitle = {Numerical {Study} of {Energy} {Deposition} {Requirements} for {Aerodynamic} {Control} of {Hypersonic} {Vehicles}},\n\tpublisher = {\\{AIAA Paper\\} 2008-1109},\n\tauthor = {Bisek, N J and Boyd, I D and Poggie, J},\n\tmonth = jan,\n\tyear = {2008},\n}\n\n\n\n
\n
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\n \n\n \n \n Pazder, J. S; Vogiatzis, K.; and Angeli, G. Z\n\n\n \n \n \n \n Dome and mirror seeing estimates for the Thirty Meter Telescope.\n \n \n \n\n\n \n\n\n\n In volume 7017, pages 229–237, Marseille, France, July 2008. SPIE\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{pazder2008,\n\taddress = {Marseille, France},\n\ttitle = {Dome and mirror seeing estimates for the {Thirty} {Meter} {Telescope}},\n\tvolume = {7017},\n\tpublisher = {SPIE},\n\tauthor = {Pazder, John S and Vogiatzis, Konstantinos and Angeli, George Z},\n\tmonth = jul,\n\tyear = {2008},\n\tpages = {229--237},\n}\n\n\n\n
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\n \n\n \n \n Bodony, D. J.; and Lele, S. K.\n\n\n \n \n \n \n Current status of jet noise predictions using large-eddy simulation.\n \n \n \n\n\n \n\n\n\n AIAA Journal, 46(2): 364–380. 2008.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{bodony2008,\n\ttitle = {Current status of jet noise predictions using large-eddy simulation},\n\tvolume = {46},\n\tdoi = {10.2514/1.24475},\n\tabstract = {A survey of the current applications of large-eddy simulation for the prediction of noise from single stream turbulent jets is given. After summarizing the numerical techniques used, the data predicted by the simulations are given at conditions from subsonic, heated jets to supersonic, unheated jets. Mach numbers between 0.3 and 2.0 are considered. Following the data presentation, an analysis of the trends exhibited by the data is given, with special attention paid to relationship between numerical and/or modeling choices and the prediction accuracy. The data support the conclusion that the most limiting factor in current large-eddy simulations is the thickness of the initial shear layer, which is commonly one order of magnitude thicker than what is found experimentally. There is also a large amount of uncertainty regarding the influence of the subgrid scale model on the predictions. The influence of inflow conditions is discussed in depth. Uncertainties in the inflow conditions currently prohibit the simulations from reliably predicting the potential core length. The centerline evolution of the mean and fluctuating axial velocity is strongly coupled to the resolution of the initial shear layers, but can be made to agree within experimental uncertainty when sufficiently thin initial shear layers are used. The maximum achieved Strouhal number of the sound in the acoustic far field is 1.5-3.0, depending on flow condition; this limit is due to numerical resources. A listing of some of the open questions and future directions concerning jet noise predictions using large-eddy simulation concludes the survey. Copyright © 2007 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.},\n\tnumber = {2},\n\tjournal = {AIAA Journal},\n\tauthor = {Bodony, Daniel J. and Lele, Sanjiva K.},\n\tyear = {2008},\n\tpages = {364--380},\n}\n\n\n\n
\n
\n\n\n
\n A survey of the current applications of large-eddy simulation for the prediction of noise from single stream turbulent jets is given. After summarizing the numerical techniques used, the data predicted by the simulations are given at conditions from subsonic, heated jets to supersonic, unheated jets. Mach numbers between 0.3 and 2.0 are considered. Following the data presentation, an analysis of the trends exhibited by the data is given, with special attention paid to relationship between numerical and/or modeling choices and the prediction accuracy. The data support the conclusion that the most limiting factor in current large-eddy simulations is the thickness of the initial shear layer, which is commonly one order of magnitude thicker than what is found experimentally. There is also a large amount of uncertainty regarding the influence of the subgrid scale model on the predictions. The influence of inflow conditions is discussed in depth. Uncertainties in the inflow conditions currently prohibit the simulations from reliably predicting the potential core length. The centerline evolution of the mean and fluctuating axial velocity is strongly coupled to the resolution of the initial shear layers, but can be made to agree within experimental uncertainty when sufficiently thin initial shear layers are used. The maximum achieved Strouhal number of the sound in the acoustic far field is 1.5-3.0, depending on flow condition; this limit is due to numerical resources. A listing of some of the open questions and future directions concerning jet noise predictions using large-eddy simulation concludes the survey. Copyright © 2007 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.\n
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\n \n\n \n \n Glass, D. E.\n\n\n \n \n \n \n \n Ceramic matrix composite (CMC) thermal protection systems (TPS) and hot structures for hypersonic vehicles.\n \n \n \n \n\n\n \n\n\n\n In 2008. American Institute of Aeronautics and Astronautics Inc.\n \n\n\n\n
\n\n\n\n \n \n \"CeramicPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{glass2008,\n\ttitle = {Ceramic matrix composite ({CMC}) thermal protection systems ({TPS}) and hot structures for hypersonic vehicles},\n\tisbn = {978-1-56347-960-1},\n\turl = {http://arc.aiaa.org},\n\tdoi = {10.2514/6.2008-2682},\n\tabstract = {Thermal protection systems (TPS) and hot structures are required for a range of hypersonic vehicles ranging from ballistic reentry to hypersonic cruise vehicles, both within Earth's atmosphere and non-Earth atmospheres. The focus of this paper is on air breathing hypersonic vehicles in the Earth's atmosphere. This includes single-stage to orbit (SSTO), two-stage to orbit (TSTO) accelerators, access to space vehicles, and hypersonic cruise vehicles. This paper will start out with a brief discussion of aerodynamic heating and thermal management techniques to address the high heating, followed by an overview of TPS for rocket-launched and air-breathing vehicles. The argument is presented that as we move from rocket-based vehicles to air-breathing vehicles, we need to move away from the "insulated airplane" approach used on the Space Shuttle Orbiter to a wide range of TPS and hot structure approaches. The primary portion of the paper will discuss issues and design options for CMC TPS and hot structure components, including leading edges, acreage TPS, and control surfaces. The current state-of-the-art will be briefly discussed for some of the components. The two primary technical challenges impacting the use of CMC TPS and hot structures for hypersonic vehicles are environmental durability and fabrication, and will be discussed briefly.},\n\tpublisher = {American Institute of Aeronautics and Astronautics Inc.},\n\tauthor = {Glass, David E.},\n\tyear = {2008},\n}\n\n\n\n
\n
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\n Thermal protection systems (TPS) and hot structures are required for a range of hypersonic vehicles ranging from ballistic reentry to hypersonic cruise vehicles, both within Earth's atmosphere and non-Earth atmospheres. The focus of this paper is on air breathing hypersonic vehicles in the Earth's atmosphere. This includes single-stage to orbit (SSTO), two-stage to orbit (TSTO) accelerators, access to space vehicles, and hypersonic cruise vehicles. This paper will start out with a brief discussion of aerodynamic heating and thermal management techniques to address the high heating, followed by an overview of TPS for rocket-launched and air-breathing vehicles. The argument is presented that as we move from rocket-based vehicles to air-breathing vehicles, we need to move away from the \"insulated airplane\" approach used on the Space Shuttle Orbiter to a wide range of TPS and hot structure approaches. The primary portion of the paper will discuss issues and design options for CMC TPS and hot structure components, including leading edges, acreage TPS, and control surfaces. The current state-of-the-art will be briefly discussed for some of the components. The two primary technical challenges impacting the use of CMC TPS and hot structures for hypersonic vehicles are environmental durability and fabrication, and will be discussed briefly.\n
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\n \n\n \n \n Siegenthaler, J.; Jumper, E.; and Gordeyev, S.\n\n\n \n \n \n \n Atmospheric Propagation vs. Aero-Optics.\n \n \n \n\n\n \n\n\n\n In Reno, Nevada, January 2008. AIAA 2008-1076\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{siegenthaler2008,\n\taddress = {Reno, Nevada},\n\ttitle = {Atmospheric {Propagation} vs. {Aero}-{Optics}},\n\tpublisher = {AIAA 2008-1076},\n\tauthor = {Siegenthaler, John and Jumper, Eric and Gordeyev, Stanislav},\n\tmonth = jan,\n\tyear = {2008},\n}\n\n\n\n
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\n \n\n \n \n Waithe, K. A.\n\n\n \n \n \n \n \n Application of USM3D for sonic boom prediction by utilizing a hybrid procedure.\n \n \n \n \n\n\n \n\n\n\n In Reno, NV, 2008. AIAA Paper 2008-129\n \n\n\n\n
\n\n\n\n \n \n \"ApplicationPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{waithe2008,\n\taddress = {Reno, NV},\n\ttitle = {Application of {USM3D} for sonic boom prediction by utilizing a hybrid procedure},\n\tisbn = {978-1-56347-937-3},\n\turl = {https://arc.aiaa.org/doi/abs/10.2514/6.2008-129},\n\tdoi = {10.2514/6.2008-129},\n\tabstract = {The application of USM3D, an unstructured flow solver, to predict sonic boom by using a hybrid computational fluid dynamics procedure on four configurations is presented. The first configuration is a generic wing-body-vertical. The second and third configurations are the Quiet Spike™, which is patented by Gulfstream, attached to equivalent area distributions. The fourth configuration is NASA's F15 with the Quiet Spike attached. Computations on the wing-body-vertical are compared to computational data from a structured flow solver. Computations on the Quiet Spike are compared to wind tunnel tests conducted at NASA Langley Research Center and computational data from a structured flow solver. Computations on the F-15 with the Quiet Spike are compared to flight test data obtained at NASA Dryden Flight Research Center. Results indicate that USM3D is a capable code to be used in a hybrid procedure for predicting sonic boom. Copyright © 2008 by Gulfstream Aeropace Corporation.},\n\tpublisher = {AIAA Paper 2008-129},\n\tauthor = {Waithe, Kenrick A.},\n\tyear = {2008},\n}\n\n\n\n
\n
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\n The application of USM3D, an unstructured flow solver, to predict sonic boom by using a hybrid computational fluid dynamics procedure on four configurations is presented. The first configuration is a generic wing-body-vertical. The second and third configurations are the Quiet Spike™, which is patented by Gulfstream, attached to equivalent area distributions. The fourth configuration is NASA's F15 with the Quiet Spike attached. Computations on the wing-body-vertical are compared to computational data from a structured flow solver. Computations on the Quiet Spike are compared to wind tunnel tests conducted at NASA Langley Research Center and computational data from a structured flow solver. Computations on the F-15 with the Quiet Spike are compared to flight test data obtained at NASA Dryden Flight Research Center. Results indicate that USM3D is a capable code to be used in a hybrid procedure for predicting sonic boom. Copyright © 2008 by Gulfstream Aeropace Corporation.\n
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\n \n\n \n \n Kim, M.; Keidar, M.; and Boyd, I. D\n\n\n \n \n \n \n Analysis of an Electromagnetic Mitigation Scheme for Reentry Telemetry Through Plasma.\n \n \n \n\n\n \n\n\n\n Journal of Spacecraft and Rockets, 45(6): 1223–1229. 2008.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{kim2008,\n\ttitle = {Analysis of an {Electromagnetic} {Mitigation} {Scheme} for {Reentry} {Telemetry} {Through} {Plasma}},\n\tvolume = {45},\n\tnumber = {6},\n\tjournal = {Journal of Spacecraft and Rockets},\n\tauthor = {Kim, Minkwan and Keidar, Michael and Boyd, Iain D},\n\tyear = {2008},\n\tpages = {1223--1229},\n}\n\n\n\n
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\n \n\n \n \n Nemec, M.; Aftosmis, M. J.; and Wintzer, M.\n\n\n \n \n \n \n Adjoint-based adaptive mesh refinement for complex geometries.\n \n \n \n\n\n \n\n\n\n In Reno, NV, 2008. \n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{nemec2008,\n\taddress = {Reno, NV},\n\ttitle = {Adjoint-based adaptive mesh refinement for complex geometries},\n\tisbn = {978-1-56347-937-3},\n\tdoi = {10.2514/6.2008-725},\n\tabstract = {This paper examines the robustness and efficiency of an adjoint-based mesh adaptation method for problems with complicated geometries. The method is used to drive cell refinement in an embedded-boundary Cartesian mesh approach for the solution of the three-dimensional Euler equations. Detailed studies of error distributions and the evolution of cell-wise error histograms with mesh refinement are used to formulate an adaptation strategy that minimizes the run-time of the flow simulation. The effectiveness of this methodology for controlling discretization errors in engineering functionals of nonsmooth problems is demonstrated using several test cases in two and three dimensions. The test cases include a model problem for sonic-boom applications and parametric studies of launch-vehicle configurations over a wide range of flight conditions. The results show that the method is well-suited for the generation of aerodynamic databases of prescribed quality without user intervention.},\n\tauthor = {Nemec, Marian and Aftosmis, Michael J. and Wintzer, Mathias},\n\tyear = {2008},\n}\n\n\n\n
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\n This paper examines the robustness and efficiency of an adjoint-based mesh adaptation method for problems with complicated geometries. The method is used to drive cell refinement in an embedded-boundary Cartesian mesh approach for the solution of the three-dimensional Euler equations. Detailed studies of error distributions and the evolution of cell-wise error histograms with mesh refinement are used to formulate an adaptation strategy that minimizes the run-time of the flow simulation. The effectiveness of this methodology for controlling discretization errors in engineering functionals of nonsmooth problems is demonstrated using several test cases in two and three dimensions. The test cases include a model problem for sonic-boom applications and parametric studies of launch-vehicle configurations over a wide range of flight conditions. The results show that the method is well-suited for the generation of aerodynamic databases of prescribed quality without user intervention.\n
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\n  \n 2007\n \n \n (19)\n \n \n
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\n \n\n \n \n Candler, G.; Barnhardt, M.; Drayna, T.; Nompelis, I.; Peterson, D.; and Subbareddy, P.\n\n\n \n \n \n \n \n Unstructured Grid Approaches for Accurate Aeroheating Simulations.\n \n \n \n \n\n\n \n\n\n\n In 18th AIAA Computational Fluid Dynamics Conference, Miami, Florida, June 2007. American Institute of Aeronautics and Astronautics\n \n\n\n\n
\n\n\n\n \n \n \"UnstructuredPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{candler_unstructured_2007,\n\taddress = {Miami, Florida},\n\ttitle = {Unstructured {Grid} {Approaches} for {Accurate} {Aeroheating} {Simulations}},\n\tisbn = {978-1-62410-129-8},\n\turl = {https://arc.aiaa.org/doi/10.2514/6.2007-3959},\n\tdoi = {10.2514/6.2007-3959},\n\tlanguage = {en},\n\turldate = {2025-03-04},\n\tbooktitle = {18th {AIAA} {Computational} {Fluid} {Dynamics} {Conference}},\n\tpublisher = {American Institute of Aeronautics and Astronautics},\n\tauthor = {Candler, Graham and Barnhardt, Michael and Drayna, Travis and Nompelis, Ioannis and Peterson, David and Subbareddy, Pramod},\n\tmonth = jun,\n\tyear = {2007},\n}\n\n\n\n
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\n \n\n \n \n Candler, G. V.\n\n\n \n \n \n \n Nonequilibrium Hypersonic Flows and Hypersonic Nozzle Flow Modeling.\n \n \n \n\n\n \n\n\n\n Technical Report STO-AVT-325-VKI, 2007.\n \n\n\n\n
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@techreport{candler2007a,\n\ttitle = {Nonequilibrium {Hypersonic} {Flows} and {Hypersonic} {Nozzle} {Flow} {Modeling}},\n\tnumber = {STO-AVT-325-VKI},\n\tauthor = {Candler, Graham V.},\n\tyear = {2007},\n}\n\n\n\n
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\n \n\n \n \n Irikura, K. K.\n\n\n \n \n \n \n Experimental Vibrational Zero-Point Energies: Diatomic Molecules.\n \n \n \n\n\n \n\n\n\n Journal of Physical and Chemical Reference Data, 36(2): 389–397. 2007.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@article{irikura_experimental_2007,\n\ttitle = {Experimental {Vibrational} {Zero}-{Point} {Energies}: {Diatomic} {Molecules}},\n\tvolume = {36},\n\tdoi = {10.1063/1.2436891},\n\tnumber = {2},\n\tjournal = {Journal of Physical and Chemical Reference Data},\n\tauthor = {Irikura, Karl K.},\n\tyear = {2007},\n\tpages = {389--397},\n}\n\n\n\n
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\n \n\n \n \n Candler, G.; Barnhardt, M.; Drayna, T.; Nompelis, I.; Peterson, D.; and Subbareddy, P.\n\n\n \n \n \n \n Unstructured Grid Approaches for Accurate Aeroheating Simulations.\n \n \n \n\n\n \n\n\n\n In 18th AIAA Computational Fluid Dynamics Conference, 2007. AIAA Paper 2007-3959\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@inproceedings{candler2007,\n\ttitle = {Unstructured {Grid} {Approaches} for {Accurate} {Aeroheating} {Simulations}},\n\tdoi = {6.2007-3959},\n\turldate = {2024-05-27},\n\tbooktitle = {18th {AIAA} {Computational} {Fluid} {Dynamics} {Conference}},\n\tpublisher = {AIAA Paper 2007-3959},\n\tauthor = {Candler, Graham and Barnhardt, Michael and Drayna, Travis and Nompelis, Ioannis and Peterson, David and Subbareddy, Pramod},\n\tyear = {2007},\n}\n\n\n\n\n\n\n\n\n\n\n\n
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\n \n\n \n \n Fan, S.; Zhang, L.; Xu, Y.; Cheng, L.; Lou, J.; Zhang, J.; and Yu, L.\n\n\n \n \n \n \n Microstructure and properties of 3D needle-punched carbon/silicon carbide brake materials.\n \n \n \n\n\n \n\n\n\n Composites Science and Technology, 67(11): 2390–2398. September 2007.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{fan_microstructure_2007,\n\ttitle = {Microstructure and properties of {3D} needle-punched carbon/silicon carbide brake materials},\n\tvolume = {67},\n\tissn = {0266-3538},\n\tdoi = {10.1016/j.compscitech.2007.01.008},\n\tabstract = {The carbon/silicon carbide brake materials were prepared by chemical vapor infiltration (CVI) combined with liquid melt infiltration (LMI). The carbon fiber preform was fabricated with the three dimension needling method. The microstructure, mechanical, thermophysical, and frictional properties of C/SiC composites were investigated. The results indicated that the composites were composed of 65wt\\%C, 27wt\\%SiC, and 8wt\\%Si. The density and porosity were 2.1gcm−3 and 4.4\\%, respectively. The C/SiC brake materials exhibited excellent toughness. The average dynamic friction coefficient and static friction coefficient of the materials were about 0.34 and 0.41, respectively. The friction coefficient was stable. The fade ratio of the friction coefficient under moist conditions was about 2.9\\%. The linear wear rate was less than 1.9μmside−1cycle−1. These results show that C/SiC composites have excellent properties for use as brake materials for aircraft.},\n\tnumber = {11},\n\turldate = {2023-10-30},\n\tjournal = {Composites Science and Technology},\n\tauthor = {Fan, Shangwu and Zhang, Litong and Xu, Yongdong and Cheng, Laifei and Lou, Jianjun and Zhang, Junzhan and Yu, Lin},\n\tmonth = sep,\n\tyear = {2007},\n\tkeywords = {A. Ceramic-matrix composites, B. Friction/wear, B. Mechanical properties, B. Microstructure, E. Liquid melt infiltration},\n\tpages = {2390--2398},\n}\n\n\n\n
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\n The carbon/silicon carbide brake materials were prepared by chemical vapor infiltration (CVI) combined with liquid melt infiltration (LMI). The carbon fiber preform was fabricated with the three dimension needling method. The microstructure, mechanical, thermophysical, and frictional properties of C/SiC composites were investigated. The results indicated that the composites were composed of 65wt%C, 27wt%SiC, and 8wt%Si. The density and porosity were 2.1gcm−3 and 4.4%, respectively. The C/SiC brake materials exhibited excellent toughness. The average dynamic friction coefficient and static friction coefficient of the materials were about 0.34 and 0.41, respectively. The friction coefficient was stable. The fade ratio of the friction coefficient under moist conditions was about 2.9%. The linear wear rate was less than 1.9μmside−1cycle−1. These results show that C/SiC composites have excellent properties for use as brake materials for aircraft.\n
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\n \n\n \n \n Wright, M. J; Hwang, H H; and Schwenke, D. W\n\n\n \n \n \n \n Recommended Collision Integrals for Transport Property Computations, Part 2: Mars and Venus Entries.\n \n \n \n\n\n \n\n\n\n AIAA Journal, 45(1): 281–288. 2007.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{wright2007a,\n\ttitle = {Recommended {Collision} {Integrals} for {Transport} {Property} {Computations}, {Part} 2: {Mars} and {Venus} {Entries}},\n\tvolume = {45},\n\tnumber = {1},\n\tjournal = {AIAA Journal},\n\tauthor = {Wright, Michael J and Hwang, H H and Schwenke, David W},\n\tyear = {2007},\n\tpages = {281--288},\n}\n\n\n\n
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\n \n\n \n \n Scalabrin, L. C; and Boyd, I. D\n\n\n \n \n \n \n Numerical Simulations of the FIRE-II Convective and Radiative Heating Rates.\n \n \n \n\n\n \n\n\n\n In Miami, FL, June 2007. \\AIAA Paper\\ 2007-4044\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@inproceedings{scalabrin2007a,\n\taddress = {Miami, FL},\n\ttitle = {Numerical {Simulations} of the {FIRE}-{II} {Convective} and {Radiative} {Heating} {Rates}},\n\tpublisher = {\\{AIAA Paper\\} 2007-4044},\n\tauthor = {Scalabrin, Leonardo C and Boyd, Iain D},\n\tmonth = jun,\n\tyear = {2007},\n}\n\n\n\n
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\n \n\n \n \n Wang, T.; Zhao, Y.; Xu, D.; and Yang, Q.\n\n\n \n \n \n \n Numerical study of evaluating the optical quality of supersonic flow fields.\n \n \n \n\n\n \n\n\n\n Applied Optics, 46(23wang-a): 5545–5551. August 2007.\n \n\n\n\n
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@article{wang2007,\n\ttitle = {Numerical study of evaluating the optical quality of supersonic flow fields},\n\tvolume = {46},\n\tnumber = {23wang-a},\n\tjournal = {Applied Optics},\n\tauthor = {Wang, Tao and Zhao, Yan and Xu, Dong and Yang, Qiuying},\n\tmonth = aug,\n\tyear = {2007},\n\tpages = {5545--5551},\n}\n\n\n\n
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\n \n\n \n \n Scalabrin, L. C\n\n\n \n \n \n \n Numerical Simulation of Weakly Ionized Hypersonic Flow over Reentry Capsules.\n \n \n \n\n\n \n\n\n\n . 2007.\n Place: Ann Arbor\n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{scalabrin2007,\n\ttitle = {Numerical {Simulation} of {Weakly} {Ionized} {Hypersonic} {Flow} over {Reentry} {Capsules}},\n\tauthor = {Scalabrin, Leonardo C},\n\tyear = {2007},\n\tnote = {Place: Ann Arbor},\n}\n\n\n\n
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\n \n\n \n \n Boyd, I. D\n\n\n \n \n \n \n \n Modeling of associative ionization reactions in hypersonic rarefied flows.\n \n \n \n \n\n\n \n\n\n\n Physics of Fluids, 19(9): 96102–96102. 2007.\n \n\n\n\n
\n\n\n\n \n \n \"ModelingPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{boyd2007,\n\ttitle = {Modeling of associative ionization reactions in hypersonic rarefied flows},\n\tvolume = {19},\n\turl = {https://doi.org/10.1063/1.2771662},\n\tdoi = {10.1063/1.2771662},\n\tnumber = {9},\n\tjournal = {Physics of Fluids},\n\tauthor = {Boyd, Iain D},\n\tyear = {2007},\n\tpages = {96102--96102},\n}\n\n\n\n
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\n \n\n \n \n Hash, D.; Olejniczak, J.; Wright, M.; Prabhu, D.; Hollis, M. P. B.; Gnoffo, P.; Barnhardt, M.; Nompelis, I.; and Candler, G.\n\n\n \n \n \n \n FIRE II Calculations for Hypersonic Nonequilibrium Aerothermodynamics Code Verification: DPLR, LAURA, and US3D.\n \n \n \n\n\n \n\n\n\n In Reno, NV, 2007. \\AIAA Paper\\ 2007-605\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{hash2007,\n\taddress = {Reno, NV},\n\ttitle = {{FIRE} {II} {Calculations} for {Hypersonic} {Nonequilibrium} {Aerothermodynamics} {Code} {Verification}: {DPLR}, {LAURA}, and {US3D}},\n\tpublisher = {\\{AIAA Paper\\} 2007-605},\n\tauthor = {Hash, David and Olejniczak, Joseph and Wright, Michael and Prabhu, Dinesh and Hollis, Maria Pulsonetti Brian and Gnoffo, Peter and Barnhardt, Michael and Nompelis, Ioannis and Candler, Graham},\n\tyear = {2007},\n}\n\n\n\n
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\n \n\n \n \n Murman, S. M.; and Aftosmis, M. J.\n\n\n \n \n \n \n \n Dynamic analysis of atmospheric-entry probes and capsules.\n \n \n \n \n\n\n \n\n\n\n In volume 2, pages 815–832, 2007. AIAA Paper 2007-0074\n \n\n\n\n
\n\n\n\n \n \n \"DynamicPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{murman2007,\n\ttitle = {Dynamic analysis of atmospheric-entry probes and capsules},\n\tvolume = {2},\n\tisbn = {1-56347-890-0},\n\turl = {https://arc.aiaa.org/doi/10.2514/6.2007-74},\n\tdoi = {10.2514/6.2007-74},\n\tabstract = {A Computational Fluid Dynamics analysis of the dynamics of probe and capsule shapes at supersonic flight conditions is performed using an automated, inviscid Cartesian-mesh scheme. This analysis uses static and dynamic free-oscillation simulations to develop static and dynamic aerodynamic coefficients for three configurations: the Viking, Genesis, and Mars Exploration Rover capsules. These computed coefficients are compared against data reduced from ballistic-range free-flight testing. A comparison of data reduction methods for capsule shapes from computational simulations and range data is included. Free-flight simulations agree well with available flight data for both fully-coupled simulations and aerodynamic database fly-throughs based on the developed aerodynamic coefficients. A sensitivity analysis of the aerodynamic coefficients for trajectory simulations at constant altitude is included. Copyright © 2007 by the American Institute of Aeronautics and Astronautics, Inc.},\n\tpublisher = {AIAA Paper 2007-0074},\n\tauthor = {Murman, Scott M. and Aftosmis, Michael J.},\n\tyear = {2007},\n\tpages = {815--832},\n}\n\n\n\n
\n
\n\n\n
\n A Computational Fluid Dynamics analysis of the dynamics of probe and capsule shapes at supersonic flight conditions is performed using an automated, inviscid Cartesian-mesh scheme. This analysis uses static and dynamic free-oscillation simulations to develop static and dynamic aerodynamic coefficients for three configurations: the Viking, Genesis, and Mars Exploration Rover capsules. These computed coefficients are compared against data reduced from ballistic-range free-flight testing. A comparison of data reduction methods for capsule shapes from computational simulations and range data is included. Free-flight simulations agree well with available flight data for both fully-coupled simulations and aerodynamic database fly-throughs based on the developed aerodynamic coefficients. A sensitivity analysis of the aerodynamic coefficients for trajectory simulations at constant altitude is included. Copyright © 2007 by the American Institute of Aeronautics and Astronautics, Inc.\n
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\n \n\n \n \n Murman, S. M.; and Aftosmis, M. J.\n\n\n \n \n \n \n \n Dynamic analysis of atmospheric-entry probes and capsules.\n \n \n \n \n\n\n \n\n\n\n In volume 2, pages 815–832, 2007. AIAA Paper 2007-0074\n \n\n\n\n
\n\n\n\n \n \n \"DynamicPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{murman2007a,\n\ttitle = {Dynamic analysis of atmospheric-entry probes and capsules},\n\tvolume = {2},\n\tisbn = {1-56347-890-0},\n\turl = {https://arc.aiaa.org/doi/10.2514/6.2007-74},\n\tdoi = {10.2514/6.2007-74},\n\tabstract = {A Computational Fluid Dynamics analysis of the dynamics of probe and capsule shapes at supersonic flight conditions is performed using an automated, inviscid Cartesian-mesh scheme. This analysis uses static and dynamic free-oscillation simulations to develop static and dynamic aerodynamic coefficients for three configurations: the Viking, Genesis, and Mars Exploration Rover capsules. These computed coefficients are compared against data reduced from ballistic-range free-flight testing. A comparison of data reduction methods for capsule shapes from computational simulations and range data is included. Free-flight simulations agree well with available flight data for both fully-coupled simulations and aerodynamic database fly-throughs based on the developed aerodynamic coefficients. A sensitivity analysis of the aerodynamic coefficients for trajectory simulations at constant altitude is included. Copyright © 2007 by the American Institute of Aeronautics and Astronautics, Inc.},\n\tpublisher = {AIAA Paper 2007-0074},\n\tauthor = {Murman, Scott M. and Aftosmis, Michael J.},\n\tyear = {2007},\n\tpages = {815--832},\n}\n\n\n\n
\n
\n\n\n
\n A Computational Fluid Dynamics analysis of the dynamics of probe and capsule shapes at supersonic flight conditions is performed using an automated, inviscid Cartesian-mesh scheme. This analysis uses static and dynamic free-oscillation simulations to develop static and dynamic aerodynamic coefficients for three configurations: the Viking, Genesis, and Mars Exploration Rover capsules. These computed coefficients are compared against data reduced from ballistic-range free-flight testing. A comparison of data reduction methods for capsule shapes from computational simulations and range data is included. Free-flight simulations agree well with available flight data for both fully-coupled simulations and aerodynamic database fly-throughs based on the developed aerodynamic coefficients. A sensitivity analysis of the aerodynamic coefficients for trajectory simulations at constant altitude is included. Copyright © 2007 by the American Institute of Aeronautics and Astronautics, Inc.\n
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\n \n\n \n \n McNamara, J. J.; Gogulapati, A.; Friedmann, P. P.; and Banavara, N. K.\n\n\n \n \n \n \n Approximate Modeling of Unsteady Aerodynamic Loads in Hypersonic Aeroelasticity.\n \n \n \n\n\n \n\n\n\n In Stockholm, 2007. \n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{mcnamara2007,\n\taddress = {Stockholm},\n\ttitle = {Approximate {Modeling} of {Unsteady} {Aerodynamic} {Loads} in {Hypersonic} {Aeroelasticity}},\n\tauthor = {McNamara, J. J. and Gogulapati, A. and Friedmann, P. P. and Banavara, N. K.},\n\tyear = {2007},\n}\n\n\n\n
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\n \n\n \n \n Góes, L. C. S.; Hemerly, E. M.; Maciel, B. C. d. O.; Neto, W. R.; Mendonca, C.; and Hoff, J.\n\n\n \n \n \n \n \n Aircraft parameter estimation using output-error methods.\n \n \n \n \n\n\n \n\n\n\n Inverse Problems in Science and Engineering, 14(6): 651–664. September 2007.\n Publisher: Taylor & Francis Group\n\n\n\n
\n\n\n\n \n \n \"AircraftPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{goes2007,\n\ttitle = {Aircraft parameter estimation using output-error methods},\n\tvolume = {14},\n\turl = {https://www.tandfonline.com/doi/abs/10.1080/17415970600573544},\n\tdoi = {10.1080/17415970600573544},\n\tabstract = {Certification requirements, optimization and minimum project costs, design of flight control laws and the implementation of flight simulators are among the principal applications of inverse problem...},\n\tnumber = {6},\n\tjournal = {Inverse Problems in Science and Engineering},\n\tauthor = {Góes, Luiz Carlos Sandoval and Hemerly, Elder Moreira and Maciel, Benedito Carlos de Oliveira and Neto, Wilson Rios and Mendonca, CelsoBraga and Hoff, João},\n\tmonth = sep,\n\tyear = {2007},\n\tnote = {Publisher: Taylor \\& Francis Group},\n\tkeywords = {Aircraft parameter estimation, Modeling and simulation, Output-error},\n\tpages = {651--664},\n}\n\n\n\n
\n
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\n Certification requirements, optimization and minimum project costs, design of flight control laws and the implementation of flight simulators are among the principal applications of inverse problem...\n
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\n \n\n \n \n Wright, M J; Grinstead, J H; and Bose, D\n\n\n \n \n \n \n A Risk-Based Approach for Aerothermal/TPS Analysis and Testing.\n \n \n \n\n\n \n\n\n\n Technical Report 2007.\n Issue: ADA476515\n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@techreport{wright2007,\n\ttitle = {A {Risk}-{Based} {Approach} for {Aerothermal}/{TPS} {Analysis} and {Testing}},\n\tauthor = {Wright, M J and Grinstead, J H and Bose, D},\n\tyear = {2007},\n\tnote = {Issue: ADA476515},\n}\n\n\n\n
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\n \n\n \n \n Schwartzentruber, T. E.; Scalabrin, L. C.; and Boyd, I. D.\n\n\n \n \n \n \n A modular particle-continuum numerical method for hypersonic non-equilibrium gas flows.\n \n \n \n\n\n \n\n\n\n Journal of Computational Physics, 225(1): 1159–1174. 2007.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{schwartzentruber2007,\n\ttitle = {A modular particle-continuum numerical method for hypersonic non-equilibrium gas flows},\n\tvolume = {225},\n\tdoi = {10.1016/j.jcp.2007.01.022},\n\tabstract = {A modular particle-continuum (MPC) numerical method for steady-state flows is presented which solves the Navier-Stokes equations in regions of near-equilibrium and uses the direct simulation Monte Carlo (DSMC) method to simulate regions of non-equilibrium gas flow. Existing, state-of-the-art, DSMC and Navier-Stokes solvers are coupled together using a novel modular implementation which requires only a limited number of additional hybrid functions. Hybrid functions are used to adaptively position particle-continuum interfaces and update boundary conditions in each module at appropriate times. The MPC method is validated for 2D flow over a cylinder at various hypersonic Mach numbers where the global Knudsen number is 0.01. For the cases considered, the MPC method is verified to accurately reproduce DSMC flow field results as well as local particle velocity distributions up to 2.2 times faster than full DSMC simulations. © 2007 Elsevier Inc. All rights reserved.},\n\tnumber = {1},\n\tjournal = {Journal of Computational Physics},\n\tauthor = {Schwartzentruber, T. E. and Scalabrin, L. C. and Boyd, I. D.},\n\tyear = {2007},\n\tkeywords = {DSMC, Direct simulation Monte Carlo, Hybrid particle-continuum, Hypersonics, Non-equilibrium flow, Rarefied flow, Re-entry vehicles},\n\tpages = {1159--1174},\n}\n\n\n\n
\n
\n\n\n
\n A modular particle-continuum (MPC) numerical method for steady-state flows is presented which solves the Navier-Stokes equations in regions of near-equilibrium and uses the direct simulation Monte Carlo (DSMC) method to simulate regions of non-equilibrium gas flow. Existing, state-of-the-art, DSMC and Navier-Stokes solvers are coupled together using a novel modular implementation which requires only a limited number of additional hybrid functions. Hybrid functions are used to adaptively position particle-continuum interfaces and update boundary conditions in each module at appropriate times. The MPC method is validated for 2D flow over a cylinder at various hypersonic Mach numbers where the global Knudsen number is 0.01. For the cases considered, the MPC method is verified to accurately reproduce DSMC flow field results as well as local particle velocity distributions up to 2.2 times faster than full DSMC simulations. © 2007 Elsevier Inc. All rights reserved.\n
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\n \n\n \n \n Gnoffo, P. A\n\n\n \n \n \n \n A Perspective on Computational Aerothermodynamics at NASA.\n \n \n \n\n\n \n\n\n\n In 2007. \n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{gnoffo2007,\n\ttitle = {A {Perspective} on {Computational} {Aerothermodynamics} at {NASA}},\n\tabstract = {The evolving role of computational aerothermodynamics (CA) within NASA over the past 20 years is reviewed. The presentation highlights contributions to understanding the Space Shuttle pitching moment anomaly observed in the first shuttle flight, prediction of a static instability for Mars Pathfinder, and the use of CA for damage assessment in post-Columbia mission-support. In the view forward, several current challenges in computational fluid dynamics and aerothermodynamics for hyper-sonic vehicle applications are discussed. Example simulations are presented to illustrate capabilities and limitations. Opportunities to advance the state-of-art in algorithms, grid generation and adaptation, and code validation are identified.},\n\tauthor = {Gnoffo, Peter A},\n\tyear = {2007},\n}\n\n\n\n
\n
\n\n\n
\n The evolving role of computational aerothermodynamics (CA) within NASA over the past 20 years is reviewed. The presentation highlights contributions to understanding the Space Shuttle pitching moment anomaly observed in the first shuttle flight, prediction of a static instability for Mars Pathfinder, and the use of CA for damage assessment in post-Columbia mission-support. In the view forward, several current challenges in computational fluid dynamics and aerothermodynamics for hyper-sonic vehicle applications are discussed. Example simulations are presented to illustrate capabilities and limitations. Opportunities to advance the state-of-art in algorithms, grid generation and adaptation, and code validation are identified.\n
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\n \n\n \n \n Thoemel, J.; Lukkien, J.; and Chazot, O.\n\n\n \n \n \n \n \n A Multiscale Approach for Building a Mechanism Based Catalysis Model for High Enthalpy Carbon Dioxide Flow.\n \n \n \n \n\n\n \n\n\n\n In Reston, Virigina, June 2007. American Institute of Aeronautics and Astronautics\n \n\n\n\n
\n\n\n\n \n \n \"APaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{thoemel2007,\n\taddress = {Reston, Virigina},\n\ttitle = {A {Multiscale} {Approach} for {Building} a {Mechanism} {Based} {Catalysis} {Model} for {High} {Enthalpy} {Carbon} {Dioxide} {Flow}},\n\tisbn = {978-1-62410-010-9},\n\turl = {https://arc.aiaa.org/doi/10.2514/6.2007-4399},\n\tdoi = {10.2514/6.2007-4399},\n\tabstract = {The principles of the gas-surface-interaction taking place in the chemically reacting flow around an atmospheric re-entry vehicle are investigated. It turns out that the currently very often used approach employing a recombination coefficient has a limited applicability. Serious concerns arise when the interaction model is extrapolated from ground to flight tests. A mechanism based approach taking into account every interaction step is therefore proposed for the carbon dioxide interaction with platinum. The necessary reaction rates are determined using a microscopic model, which are then used in a continuum viscous flow simulation. The dependence of the catalysis on the outer flow conditions and also on the wall temperature is demonstrated. Nomenclature γ recombination coefficient,-M rec number of recombining atoms, 1/(m 2 s) M ↓ number of impinging atoms, 1/(m 2 s) [X] concentration of generic species,mol/m 3 k reaction rate, m, mol, s W ads microscopic reaction rate, 1/s p pressure, P a A site area adsorption site, m 2 σ initial/microscopic sticking coefficient,1 m molecular mass, kg k b Stefan-Boltzmann constant, J/K T temperature, K u tangential velocity, m/s v perpendicular velocity, m/s h enthalpy, J/kg w mass production term, kg/m 3 , kg/m 2 c species mass f ν stochiometric coefficient Y partial pressure coefficient/ZGB parameter θ surface coverage Da Damköhler number (s) adsorption site V vacant adsorption site concentration, mol/m 2 Subscripts rec Recombining ref. reference ad Adsorption reac Reaction rel. relative ER Eley-Rideal-Mechanism LH Langmuir-Hinshelwood-Mechanism},\n\tpublisher = {American Institute of Aeronautics and Astronautics},\n\tauthor = {Thoemel, Jan and Lukkien, Johan and Chazot, Olivier},\n\tmonth = jun,\n\tyear = {2007},\n}\n\n\n\n
\n
\n\n\n
\n The principles of the gas-surface-interaction taking place in the chemically reacting flow around an atmospheric re-entry vehicle are investigated. It turns out that the currently very often used approach employing a recombination coefficient has a limited applicability. Serious concerns arise when the interaction model is extrapolated from ground to flight tests. A mechanism based approach taking into account every interaction step is therefore proposed for the carbon dioxide interaction with platinum. The necessary reaction rates are determined using a microscopic model, which are then used in a continuum viscous flow simulation. The dependence of the catalysis on the outer flow conditions and also on the wall temperature is demonstrated. Nomenclature γ recombination coefficient,-M rec number of recombining atoms, 1/(m 2 s) M ↓ number of impinging atoms, 1/(m 2 s) [X] concentration of generic species,mol/m 3 k reaction rate, m, mol, s W ads microscopic reaction rate, 1/s p pressure, P a A site area adsorption site, m 2 σ initial/microscopic sticking coefficient,1 m molecular mass, kg k b Stefan-Boltzmann constant, J/K T temperature, K u tangential velocity, m/s v perpendicular velocity, m/s h enthalpy, J/kg w mass production term, kg/m 3 , kg/m 2 c species mass f ν stochiometric coefficient Y partial pressure coefficient/ZGB parameter θ surface coverage Da Damköhler number (s) adsorption site V vacant adsorption site concentration, mol/m 2 Subscripts rec Recombining ref. reference ad Adsorption reac Reaction rel. relative ER Eley-Rideal-Mechanism LH Langmuir-Hinshelwood-Mechanism\n
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\n  \n 2006\n \n \n (22)\n \n \n
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\n \n\n \n \n Anderson, J. D.\n\n\n \n \n \n \n Hypersonic and high-temperature gas dynamics.\n \n \n \n\n\n \n\n\n\n of AIAA education seriesAmerican Institute of Aeronautics and Astronautics, Reston, Va, 2nd ed edition, 2006.\n OCLC: ocm68262944\n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n\n\n\n
\n 
@book{anderson_hypersonic_2006,\n\taddress = {Reston, Va},\n\tedition = {2nd ed},\n\tseries = {{AIAA} education series},\n\ttitle = {Hypersonic and high-temperature gas dynamics},\n\tisbn = {978-1-56347-780-5},\n\tpublisher = {American Institute of Aeronautics and Astronautics},\n\tauthor = {Anderson, John D.},\n\tyear = {2006},\n\tnote = {OCLC: ocm68262944},\n\tkeywords = {Aerodynamics, Hypersonic},\n}\n\n\n\n\n\n\n\n
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\n \n\n \n \n Szmerekovsky, A. G.; Palazotto, A. N.; and Baker, W. P.\n\n\n \n \n \n \n Scaling numerical models for hypervelocity test sled slipper-rail impacts.\n \n \n \n\n\n \n\n\n\n International Journal of Impact Engineering, 32(6): 928–946. June 2006.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{szmerekovsky2006,\n\ttitle = {Scaling numerical models for hypervelocity test sled slipper-rail impacts},\n\tvolume = {32},\n\tdoi = {10.1016/j.ijimpeng.2004.09.011},\n\tabstract = {Hypervelocity test sled slipper-rail impacts have been simulated numerically using the finite volume hydrocode, ChartD to the Three-Halves (CTH). This study addresses the difficulties of applying CTH model solutions to real test sled runs. Past CTH models using dimensions different than actual test sleds have been used to study phenomenological aspects of the problem. However, quantitative results from the CTH model solution do not apply directly to actual test sled runs due to strain rate effects and time scale differences. The Buckingham Pi Theorem is applied to two potential hypervelocity gouging models. Validity of the invariant products is tested using sample CTH hypervelocity gouging models that are scaled up to simulate dimensions of a real test sled. Real test sled dimensions are desired in order to more closely simulate actual test sled runs. Invariant products developed from application of the Buckingham Pi Theorem can be used as guidelines for determining whether a CTH model is applicable to a test sled with specific dimensions. Strain rate effects are investigated to study whether deviations between scaled CTH models may be reduced by modifying the constitutive model.},\n\tnumber = {6},\n\turldate = {2024-06-12},\n\tjournal = {International Journal of Impact Engineering},\n\tauthor = {Szmerekovsky, A. G. and Palazotto, A. N. and Baker, W. P.},\n\tmonth = jun,\n\tyear = {2006},\n\tkeywords = {CTH, Dimensional analysis, Gouging, Hypervelocity impact, Scaling},\n\tpages = {928--946},\n}\n\n\n\n\n\n\n\n
\n
\n\n\n
\n Hypervelocity test sled slipper-rail impacts have been simulated numerically using the finite volume hydrocode, ChartD to the Three-Halves (CTH). This study addresses the difficulties of applying CTH model solutions to real test sled runs. Past CTH models using dimensions different than actual test sleds have been used to study phenomenological aspects of the problem. However, quantitative results from the CTH model solution do not apply directly to actual test sled runs due to strain rate effects and time scale differences. The Buckingham Pi Theorem is applied to two potential hypervelocity gouging models. Validity of the invariant products is tested using sample CTH hypervelocity gouging models that are scaled up to simulate dimensions of a real test sled. Real test sled dimensions are desired in order to more closely simulate actual test sled runs. Invariant products developed from application of the Buckingham Pi Theorem can be used as guidelines for determining whether a CTH model is applicable to a test sled with specific dimensions. Strain rate effects are investigated to study whether deviations between scaled CTH models may be reduced by modifying the constitutive model.\n
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\n \n\n \n \n Huang, G.; Zhu, Q.; and Siew, C.\n\n\n \n \n \n \n Extreme learning machine: Theory and applications.\n \n \n \n\n\n \n\n\n\n Neurocomputing, 70(1): 489–501. December 2006.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{huang2006,\n\tseries = {Neural {Networks}},\n\ttitle = {Extreme learning machine: {Theory} and applications},\n\tvolume = {70},\n\tissn = {0925-2312},\n\tshorttitle = {Extreme learning machine},\n\tdoi = {10.1016/j.neucom.2005.12.126},\n\tabstract = {It is clear that the learning speed of feedforward neural networks is in general far slower than required and it has been a major bottleneck in their applications for past decades. Two key reasons behind may be: (1) the slow gradient-based learning algorithms are extensively used to train neural networks, and (2) all the parameters of the networks are tuned iteratively by using such learning algorithms. Unlike these conventional implementations, this paper proposes a new learning algorithm called extreme learning machine (ELM) for single-hidden layer feedforward neural networks (SLFNs) which randomly chooses hidden nodes and analytically determines the output weights of SLFNs. In theory, this algorithm tends to provide good generalization performance at extremely fast learning speed. The experimental results based on a few artificial and real benchmark function approximation and classification problems including very large complex applications show that the new algorithm can produce good generalization performance in most cases and can learn thousands of times faster than conventional popular learning algorithms for feedforward neural networks.11For the preliminary idea of the ELM algorithm, refer to “Extreme Learning Machine: A New Learning Scheme of Feedforward Neural Networks”, Proceedings of International Joint Conference on Neural Networks (IJCNN2004), Budapest, Hungary, 25–29 July, 2004.},\n\tnumber = {1},\n\turldate = {2024-04-24},\n\tjournal = {Neurocomputing},\n\tauthor = {Huang, Guang-Bin and Zhu, Qin-Yu and Siew, Chee-Kheong},\n\tmonth = dec,\n\tyear = {2006},\n\tkeywords = {Back-propagation algorithm, Extreme learning machine, Feedforward neural networks, Random node, Real-time learning, Support vector machine},\n\tpages = {489--501},\n}\n\n\n\n\n\n\n\n
\n
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\n It is clear that the learning speed of feedforward neural networks is in general far slower than required and it has been a major bottleneck in their applications for past decades. Two key reasons behind may be: (1) the slow gradient-based learning algorithms are extensively used to train neural networks, and (2) all the parameters of the networks are tuned iteratively by using such learning algorithms. Unlike these conventional implementations, this paper proposes a new learning algorithm called extreme learning machine (ELM) for single-hidden layer feedforward neural networks (SLFNs) which randomly chooses hidden nodes and analytically determines the output weights of SLFNs. In theory, this algorithm tends to provide good generalization performance at extremely fast learning speed. The experimental results based on a few artificial and real benchmark function approximation and classification problems including very large complex applications show that the new algorithm can produce good generalization performance in most cases and can learn thousands of times faster than conventional popular learning algorithms for feedforward neural networks.11For the preliminary idea of the ELM algorithm, refer to “Extreme Learning Machine: A New Learning Scheme of Feedforward Neural Networks”, Proceedings of International Joint Conference on Neural Networks (IJCNN2004), Budapest, Hungary, 25–29 July, 2004.\n
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\n \n\n \n \n Bogard, D. G.; and Thole, K. A.\n\n\n \n \n \n \n Gas Turbine Film Cooling.\n \n \n \n\n\n \n\n\n\n Journal of Propulsion and Power, 22(2): 249–270. 2006.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{bogard2006,\n\ttitle = {Gas {Turbine} {Film} {Cooling}},\n\tvolume = {22},\n\tissn = {0748-4658},\n\tdoi = {10.2514/1.18034},\n\tnumber = {2},\n\turldate = {2024-01-24},\n\tjournal = {Journal of Propulsion and Power},\n\tauthor = {Bogard, D. G. and Thole, K. A.},\n\tyear = {2006},\n\tpages = {249--270},\n}\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n
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\n \n\n \n \n Smits, A.; Martin, M. P.; Wu, M; and Ringuette, M\n\n\n \n \n \n \n The Turbulence Structure of Shockwave and Boundary Layer Interactions in a Compression Corner.\n \n \n \n\n\n \n\n\n\n In 44th AIAA Aerospace Sciences Meeting and Exhibit, Reno, Nevada, January 2006. AIAA Paper 2006-497\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{smits2006,\n\taddress = {Reno, Nevada},\n\ttitle = {The {Turbulence} {Structure} of {Shockwave} and {Boundary} {Layer} {Interactions} in a {Compression} {Corner}},\n\tisbn = {978-1-62410-039-0},\n\tdoi = {10.2514/6.2006-497},\n\tlanguage = {en},\n\turldate = {2023-08-09},\n\tbooktitle = {44th {AIAA} {Aerospace} {Sciences} {Meeting} and {Exhibit}},\n\tpublisher = {AIAA Paper 2006-497},\n\tauthor = {Smits, Alexander and Martin, M. Pino and Wu, M and Ringuette, M},\n\tmonth = jan,\n\tyear = {2006},\n}\n\n\n\n\n\n\n\n
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\n \n\n \n \n Johnson, H.; and Candler, G.\n\n\n \n \n \n \n Analysis of Laminar-Turbulent Transition in Hypersonic Flight Using PSE-Chem.\n \n \n \n\n\n \n\n\n\n In 36th AIAA Fluid Dynamics Conference and Exhibit, San Francisco, California, June 2006. AIAA Paper 2006-3057\n \n\n\n\n
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\n 
@inproceedings{johnson2006,\n\taddress = {San Francisco, California},\n\ttitle = {Analysis of {Laminar}-{Turbulent} {Transition} in {Hypersonic} {Flight} {Using} {PSE}-{Chem}},\n\tisbn = {978-1-62410-033-8},\n\tdoi = {10.2514/6.2006-3057},\n\tlanguage = {en},\n\turldate = {2023-08-08},\n\tbooktitle = {36th {AIAA} {Fluid} {Dynamics} {Conference} and {Exhibit}},\n\tpublisher = {AIAA Paper 2006-3057},\n\tauthor = {Johnson, Heath and Candler, Graham},\n\tmonth = jun,\n\tyear = {2006},\n}\n\n\n\n\n\n\n\n
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\n \n\n \n \n Rasmussen, C. E.; and Williams, C.\n\n\n \n \n \n \n Gaussian Processes for Machine Learning.\n \n \n \n\n\n \n\n\n\n The MIT Press, 2006.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@book{rasmussen2006,\n\ttitle = {Gaussian {Processes} for {Machine} {Learning}},\n\tpublisher = {The MIT Press},\n\tauthor = {Rasmussen, Carl Edward and Williams, Christopher},\n\tyear = {2006},\n}\n\n\n\n
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\n \n\n \n \n Voland, R. T.; Huebner, L. D.; and McClinton, C. R.\n\n\n \n \n \n \n X-43A Hypersonic vehicle technology development.\n \n \n \n\n\n \n\n\n\n Acta Astronautica, 59(1-5): 181–191. July 2006.\n Publisher: Pergamon\n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{voland2006,\n\ttitle = {X-{43A} {Hypersonic} vehicle technology development},\n\tvolume = {59},\n\tissn = {00945765},\n\tdoi = {10.1016/j.actaastro.2006.02.021},\n\tabstract = {NASA recently completed two major programs in hypersonics: Hyper-X, with the record-breaking flights of the X-43A, and the next generation launch technology (NGLT) program. The X-43A flights, the culmination of the Hyper-X program, were the first-ever examples of a scramjet engine propelling a hypersonic vehicle and provided unique, convincing, detailed flight data required to validate the design tools needed for design and development of future operational hypersonic airbreathing vehicles. Concurrent with Hyper-X, NASA's NGLT program focused on technologies needed for future revolutionary launch vehicles. The NGLT was "competed" by NASA in response to the President's redirection of the agency to space exploration, after making significant progress towards maturing technologies required to enable airbreathing hypersonic launch vehicles. NGLT quantified the benefits, identified technology needs, developed airframe and propulsion technology, chartered a broad University base, and developed detailed plans to mature and validate hypersonic airbreathing technology for space access. NASA is currently in the process of defining plans for a new hypersonic technology program. Details of that plan are not currently available. This paper highlights results from the successful Mach 7 and 10 flights of the X-43A, and the current state of hypersonic technology. © 2006.},\n\tnumber = {1-5},\n\turldate = {2021-05-28},\n\tjournal = {Acta Astronautica},\n\tauthor = {Voland, Randall T. and Huebner, Lawrence D. and McClinton, Charles R.},\n\tmonth = jul,\n\tyear = {2006},\n\tnote = {Publisher: Pergamon},\n\tpages = {181--191},\n}\n\n\n\n
\n
\n\n\n
\n NASA recently completed two major programs in hypersonics: Hyper-X, with the record-breaking flights of the X-43A, and the next generation launch technology (NGLT) program. The X-43A flights, the culmination of the Hyper-X program, were the first-ever examples of a scramjet engine propelling a hypersonic vehicle and provided unique, convincing, detailed flight data required to validate the design tools needed for design and development of future operational hypersonic airbreathing vehicles. Concurrent with Hyper-X, NASA's NGLT program focused on technologies needed for future revolutionary launch vehicles. The NGLT was \"competed\" by NASA in response to the President's redirection of the agency to space exploration, after making significant progress towards maturing technologies required to enable airbreathing hypersonic launch vehicles. NGLT quantified the benefits, identified technology needs, developed airframe and propulsion technology, chartered a broad University base, and developed detailed plans to mature and validate hypersonic airbreathing technology for space access. NASA is currently in the process of defining plans for a new hypersonic technology program. Details of that plan are not currently available. This paper highlights results from the successful Mach 7 and 10 flights of the X-43A, and the current state of hypersonic technology. © 2006.\n
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\n \n\n \n \n Voland, R. T.; Huebner, L. D.; and McClinton, C. R.\n\n\n \n \n \n \n X-43A Hypersonic vehicle technology development.\n \n \n \n\n\n \n\n\n\n Acta Astronautica, 59(1-5): 181–191. July 2006.\n Publisher: Pergamon\n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{voland2006b,\n\ttitle = {X-{43A} {Hypersonic} vehicle technology development},\n\tvolume = {59},\n\tdoi = {10.1016/j.actaastro.2006.02.021},\n\tabstract = {NASA recently completed two major programs in hypersonics: Hyper-X, with the record-breaking flights of the X-43A, and the next generation launch technology (NGLT) program. The X-43A flights, the culmination of the Hyper-X program, were the first-ever examples of a scramjet engine propelling a hypersonic vehicle and provided unique, convincing, detailed flight data required to validate the design tools needed for design and development of future operational hypersonic airbreathing vehicles. Concurrent with Hyper-X, NASA's NGLT program focused on technologies needed for future revolutionary launch vehicles. The NGLT was "competed" by NASA in response to the President's redirection of the agency to space exploration, after making significant progress towards maturing technologies required to enable airbreathing hypersonic launch vehicles. NGLT quantified the benefits, identified technology needs, developed airframe and propulsion technology, chartered a broad University base, and developed detailed plans to mature and validate hypersonic airbreathing technology for space access. NASA is currently in the process of defining plans for a new hypersonic technology program. Details of that plan are not currently available. This paper highlights results from the successful Mach 7 and 10 flights of the X-43A, and the current state of hypersonic technology. © 2006.},\n\tnumber = {1-5},\n\tjournal = {Acta Astronautica},\n\tauthor = {Voland, Randall T. and Huebner, Lawrence D. and McClinton, Charles R.},\n\tmonth = jul,\n\tyear = {2006},\n\tnote = {Publisher: Pergamon},\n\tpages = {181--191},\n}\n\n\n\n
\n
\n\n\n
\n NASA recently completed two major programs in hypersonics: Hyper-X, with the record-breaking flights of the X-43A, and the next generation launch technology (NGLT) program. The X-43A flights, the culmination of the Hyper-X program, were the first-ever examples of a scramjet engine propelling a hypersonic vehicle and provided unique, convincing, detailed flight data required to validate the design tools needed for design and development of future operational hypersonic airbreathing vehicles. Concurrent with Hyper-X, NASA's NGLT program focused on technologies needed for future revolutionary launch vehicles. The NGLT was \"competed\" by NASA in response to the President's redirection of the agency to space exploration, after making significant progress towards maturing technologies required to enable airbreathing hypersonic launch vehicles. NGLT quantified the benefits, identified technology needs, developed airframe and propulsion technology, chartered a broad University base, and developed detailed plans to mature and validate hypersonic airbreathing technology for space access. NASA is currently in the process of defining plans for a new hypersonic technology program. Details of that plan are not currently available. This paper highlights results from the successful Mach 7 and 10 flights of the X-43A, and the current state of hypersonic technology. © 2006.\n
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\n \n\n \n \n White, F. M\n\n\n \n \n \n \n Viscous Fluid Flow.\n \n \n \n\n\n \n\n\n\n McGraw-Hill, New York, Third edition, 2006.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@book{white2006,\n\taddress = {New York},\n\tedition = {Third},\n\ttitle = {Viscous {Fluid} {Flow}},\n\tpublisher = {McGraw-Hill},\n\tauthor = {White, Frank M},\n\tyear = {2006},\n}\n\n\n\n
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\n \n\n \n \n Voland, R. T; Huebner, L. D; and McClinton, C. R\n\n\n \n \n \n \n X-43A Hypersonic vehicle technology development.\n \n \n \n\n\n \n\n\n\n Acta Astronautica, 59: 181–191. 2006.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{voland2006a,\n\ttitle = {X-{43A} {Hypersonic} vehicle technology development},\n\tvolume = {59},\n\tjournal = {Acta Astronautica},\n\tauthor = {Voland, Randall T and Huebner, Lawrence D and McClinton, Charles R},\n\tyear = {2006},\n\tpages = {181--191},\n}\n\n\n\n
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\n \n\n \n \n Sadiki, A.; and Janicka, J.\n\n\n \n \n \n \n Unsteady methods (URANS and LES) for simulation of combustion systems.\n \n \n \n\n\n \n\n\n\n International Journal of Thermal Sciences, 45(8): 760–773. August 2006.\n Publisher: Elsevier Masson\n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{sadiki2006,\n\ttitle = {Unsteady methods ({URANS} and {LES}) for simulation of combustion systems},\n\tvolume = {45},\n\tdoi = {10.1016/J.IJTHERMALSCI.2005.11.001},\n\tabstract = {A great variety of flows with importance to practical engineering applications are inherently unsteady, and virtually all of the Newtonian fluid flows in nature are turbulent. In order to better capture the dynamics of such complex flows using feasible computational costs, it is more appropriate to use unsteady methods. The present overview is confined to single-phase turbulent flows and discuses some basic issues related to unsteady modeling methods. The first part of this paper provides an evaluation of the performance of the unsteady RANS (URANS) method in a comparative manner to LES and experimental data. It could be confirmed that the U-RANS method employing a full Reynolds stress model is able to capture unsteady phenomena, such as the precessing vortex core phenomenon both qualitatively and in parts also quantitatively. In the second part, some important features of combustion LES are recollected and some results based on the conserved scalar method in connection with the concept of sub-grid scale pdf are presented. A flamelet approach is used to relate the filtered mixture fraction to density, temperature and species concentrations. It is shown that LES is able to deliver good results very close to available measured data, where the flow is governed by large, turbulent structures. Flamelet chemistry appears well able to reproduce experimental data for species, in particular with regard to kinetic effects prediction, whereas equilibrium chemistry strongly deviates. However, a good predictability could be achieved when appropriate choice of boundary and inflow conditions is made. The use of the technique of numerical inflow-generation appears to be very helpful.},\n\tnumber = {8},\n\tjournal = {International Journal of Thermal Sciences},\n\tauthor = {Sadiki, A. and Janicka, J.},\n\tmonth = aug,\n\tyear = {2006},\n\tnote = {Publisher: Elsevier Masson},\n\tpages = {760--773},\n}\n\n\n\n
\n
\n\n\n
\n A great variety of flows with importance to practical engineering applications are inherently unsteady, and virtually all of the Newtonian fluid flows in nature are turbulent. In order to better capture the dynamics of such complex flows using feasible computational costs, it is more appropriate to use unsteady methods. The present overview is confined to single-phase turbulent flows and discuses some basic issues related to unsteady modeling methods. The first part of this paper provides an evaluation of the performance of the unsteady RANS (URANS) method in a comparative manner to LES and experimental data. It could be confirmed that the U-RANS method employing a full Reynolds stress model is able to capture unsteady phenomena, such as the precessing vortex core phenomenon both qualitatively and in parts also quantitatively. In the second part, some important features of combustion LES are recollected and some results based on the conserved scalar method in connection with the concept of sub-grid scale pdf are presented. A flamelet approach is used to relate the filtered mixture fraction to density, temperature and species concentrations. It is shown that LES is able to deliver good results very close to available measured data, where the flow is governed by large, turbulent structures. Flamelet chemistry appears well able to reproduce experimental data for species, in particular with regard to kinetic effects prediction, whereas equilibrium chemistry strongly deviates. However, a good predictability could be achieved when appropriate choice of boundary and inflow conditions is made. The use of the technique of numerical inflow-generation appears to be very helpful.\n
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\n \n\n \n \n Jones, W T; Nielsen, E J; and Park, M A\n\n\n \n \n \n \n Validation of 3D Adjoint Based Error Estimation and Mesh Adaptation for Sonic Boom Prediction.\n \n \n \n\n\n \n\n\n\n In pages 1–20, Reno, NV, 2006. \\AIAA Paper\\ 2006-1150\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{jones2006,\n\taddress = {Reno, NV},\n\ttitle = {Validation of {3D} {Adjoint} {Based} {Error} {Estimation} and {Mesh} {Adaptation} for {Sonic} {Boom} {Prediction}},\n\tdoi = {10.2514/6.2006-1150},\n\tabstract = {A procedure used to validate a 3-D mesh adaptation scheme based on adjoint-based error estimation with application to sonic boom propagation is described. The method is based on a cost function formulation that integrates the near-field pressure differential over a prescribed surface. The uncertainty in the computation of this cost function is used to drive automatic h-r mesh adaptation such that errors in the functional are reduced without human intervention. The primary configurations used to validate the technique are a family of simple cone-cylinder geometries for which experimental data is available. Computed results for inviscid flow at Mach numbers of 1.26 and 1.41 are presented at various distances in the near-field up to 20 body lengths. These results are compared against the available test data and show good agreement.},\n\tpublisher = {\\{AIAA Paper\\} 2006-1150},\n\tauthor = {Jones, W T and Nielsen, E J and Park, M A},\n\tyear = {2006},\n\tpages = {1--20},\n}\n\n\n\n
\n
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\n A procedure used to validate a 3-D mesh adaptation scheme based on adjoint-based error estimation with application to sonic boom propagation is described. The method is based on a cost function formulation that integrates the near-field pressure differential over a prescribed surface. The uncertainty in the computation of this cost function is used to drive automatic h-r mesh adaptation such that errors in the functional are reduced without human intervention. The primary configurations used to validate the technique are a family of simple cone-cylinder geometries for which experimental data is available. Computed results for inviscid flow at Mach numbers of 1.26 and 1.41 are presented at various distances in the near-field up to 20 body lengths. These results are compared against the available test data and show good agreement.\n
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\n \n\n \n \n Park, C.\n\n\n \n \n \n \n Thermochemical Relaxation in Shock Tunnels.\n \n \n \n\n\n \n\n\n\n Journal of Thermophysics and Heat Transfer, 20(4): 689–698. 2006.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{park2006,\n\ttitle = {Thermochemical {Relaxation} in {Shock} {Tunnels}},\n\tvolume = {20},\n\tnumber = {4},\n\tjournal = {Journal of Thermophysics and Heat Transfer},\n\tauthor = {Park, Chul},\n\tyear = {2006},\n\tpages = {689--698},\n}\n\n\n\n
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\n \n\n \n \n Breiteig, T.; and Grevholm, B.\n\n\n \n \n \n \n The transition from arithmetic to algebra: to reason, explain, argue, generalize and justify.\n \n \n \n\n\n \n\n\n\n In pages 225–232, 2006. \n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{breiteig2006,\n\ttitle = {The transition from arithmetic to algebra: to reason, explain, argue, generalize and justify},\n\tauthor = {Breiteig, T. and Grevholm, B.},\n\tyear = {2006},\n\tpages = {225--232},\n}\n\n\n\n
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\n \n\n \n \n Klinkrad, H.\n\n\n \n \n \n \n Space Debris.\n \n \n \n\n\n \n\n\n\n Springer-Verlag, Berlin, 2006.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@book{klinkrad2006,\n\taddress = {Berlin},\n\ttitle = {Space {Debris}},\n\tpublisher = {Springer-Verlag},\n\tauthor = {Klinkrad, Heiner},\n\tyear = {2006},\n}\n\n\n\n
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\n \n\n \n \n Plotkin, K. J.; Franz, R. J.; and Haering, E. A.\n\n\n \n \n \n \n \n Prediction and measurement of a weak sonic boom from an entry vehicle.\n \n \n \n \n\n\n \n\n\n\n The Journal of the Acoustical Society of America, 120(5): 3077–3077. 2006.\n Publisher: Acoustical Society of America (ASA)\n\n\n\n
\n\n\n\n \n \n \"PredictionPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{plotkin2006,\n\ttitle = {Prediction and measurement of a weak sonic boom from an entry vehicle},\n\tvolume = {120},\n\turl = {http://asa.scitation.org/doi/10.1121/1.4787408},\n\tdoi = {10.1121/1.4787408},\n\tabstract = {There is a current interest in measuring low‐amplitude sonic booms in the atmosphere. This interest is related to verifying the predicted loudness and structure of the shock waves. The reentry of t...},\n\tnumber = {5},\n\tjournal = {The Journal of the Acoustical Society of America},\n\tauthor = {Plotkin, Kenneth J. and Franz, Russell J. and Haering, Edward A.},\n\tyear = {2006},\n\tnote = {Publisher: Acoustical Society of America (ASA)},\n\tpages = {3077--3077},\n}\n\n\n\n
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\n There is a current interest in measuring low‐amplitude sonic booms in the atmosphere. This interest is related to verifying the predicted loudness and structure of the shock waves. The reentry of t...\n
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\n \n\n \n \n Anderson, J. D\n\n\n \n \n \n \n Hypersonic and High-Temperature Gas Dynamics.\n \n \n \n\n\n \n\n\n\n AIAA, 2nd edition, 2006.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@book{anderson2006,\n\tedition = {2nd},\n\ttitle = {Hypersonic and {High}-{Temperature} {Gas} {Dynamics}},\n\tpublisher = {AIAA},\n\tauthor = {Anderson, John D},\n\tyear = {2006},\n}\n\n\n\n
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\n \n\n \n \n Bertin, J. J.; and Cummings, R. M.\n\n\n \n \n \n \n \n Critical Hypersonic Aerothermodynamic Phenomena.\n \n \n \n \n\n\n \n\n\n\n Annual Review of Fluid Mechanics, 38(1): 129–157. January 2006.\n Publisher: Annual Reviews\n\n\n\n
\n\n\n\n \n \n \"CriticalPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{bertin2006,\n\ttitle = {Critical {Hypersonic} {Aerothermodynamic} {Phenomena}},\n\tvolume = {38},\n\turl = {http://www.annualreviews.org/doi/10.1146/annurev.fluid.38.050304.092041},\n\tdoi = {10.1146/annurev.fluid.38.050304.092041},\n\tabstract = {The challenges in understanding hypersonic flight are discussed and critical hypersonic aerothermodynamics issues are reviewed. The ability of current analytical methods, numerical methods, ground testing capabilities, and flight testing approaches to predict hypersonic flow are evaluated. The areas where aerothermodynamic shortcomings restrict our ability to design and analyze hypersonic vehicles are discussed, and prospects for future capabilities are reviewed. Considerable work still needs to be done before our understanding of hypersonic flow will allow for the accurate prediction of vehicle flight characteristics throughout the flight envelope from launch to orbital insertion. Copyright © 2006 by Annual Reviews. All rights reserved.},\n\tnumber = {1},\n\tjournal = {Annual Review of Fluid Mechanics},\n\tauthor = {Bertin, John J. and Cummings, Russell M.},\n\tmonth = jan,\n\tyear = {2006},\n\tnote = {Publisher: Annual Reviews},\n\tkeywords = {Boundary-layer transition, CFD, Flight testing, Ground testing, Hypersonic},\n\tpages = {129--157},\n}\n\n\n\n
\n
\n\n\n
\n The challenges in understanding hypersonic flight are discussed and critical hypersonic aerothermodynamics issues are reviewed. The ability of current analytical methods, numerical methods, ground testing capabilities, and flight testing approaches to predict hypersonic flow are evaluated. The areas where aerothermodynamic shortcomings restrict our ability to design and analyze hypersonic vehicles are discussed, and prospects for future capabilities are reviewed. Considerable work still needs to be done before our understanding of hypersonic flow will allow for the accurate prediction of vehicle flight characteristics throughout the flight envelope from launch to orbital insertion. Copyright © 2006 by Annual Reviews. All rights reserved.\n
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\n \n\n \n \n Itakawa, Y\n\n\n \n \n \n \n Cross Sections for Electron Collisions with Nitrogen Molecules.\n \n \n \n\n\n \n\n\n\n Journal of Physical and Chemical Reference Data, 35(1). 2006.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{itakawa2006,\n\ttitle = {Cross {Sections} for {Electron} {Collisions} with {Nitrogen} {Molecules}},\n\tvolume = {35},\n\tnumber = {1},\n\tjournal = {Journal of Physical and Chemical Reference Data},\n\tauthor = {Itakawa, Y},\n\tyear = {2006},\n}\n\n\n\n
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\n \n\n \n \n Ferlauto, M.; and Marsilio, R.\n\n\n \n \n \n \n A viscous inverse method for aerodynamic design.\n \n \n \n\n\n \n\n\n\n Computers & Fluids, 35(3): 304–325. March 2006.\n Publisher: Pergamon\n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{ferlauto2006,\n\ttitle = {A viscous inverse method for aerodynamic design},\n\tvolume = {35},\n\tdoi = {10.1016/J.COMPFLUID.2005.01.003},\n\tabstract = {A numerical technique to solve two-dimensional inverse problems that arise in aerodynamic design is presented. The approach, which is well-established for inviscid, rotational flows, is here extended to the viscous case. Two-dimensional and axisymmetric configurations are here considered. The solution of the inverse problem is given as the steady state of an ideal transient during which the flowfield assesses itself to the boundary conditions by changing the boundary contour. Comparisons with theoretical and experimental results are used to validate the numerical procedure. © 2005 Elsevier Ltd. All rights reserved.},\n\tnumber = {3},\n\tjournal = {Computers \\& Fluids},\n\tauthor = {Ferlauto, Michele and Marsilio, Roberto},\n\tmonth = mar,\n\tyear = {2006},\n\tnote = {Publisher: Pergamon},\n\tpages = {304--325},\n}\n\n\n\n
\n
\n\n\n
\n A numerical technique to solve two-dimensional inverse problems that arise in aerodynamic design is presented. The approach, which is well-established for inviscid, rotational flows, is here extended to the viscous case. Two-dimensional and axisymmetric configurations are here considered. The solution of the inverse problem is given as the steady state of an ideal transient during which the flowfield assesses itself to the boundary conditions by changing the boundary contour. Comparisons with theoretical and experimental results are used to validate the numerical procedure. © 2005 Elsevier Ltd. All rights reserved.\n
\n\n\n
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\n \n\n \n \n Laflin, K. R.; Klausmeyer, S. M.; and Chaffin, M.\n\n\n \n \n \n \n \n A hybrid computational fluid dynamics procedure for sonic boom prediction.\n \n \n \n \n\n\n \n\n\n\n In volume 2, pages 954–965, San Francisco, CA, 2006. AIAA Paper 2006-3168\n \n\n\n\n
\n\n\n\n \n \n \"APaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{laflin2006,\n\taddress = {San Francisco, CA},\n\ttitle = {A hybrid computational fluid dynamics procedure for sonic boom prediction},\n\tvolume = {2},\n\tisbn = {1-56347-812-9},\n\turl = {https://arc.aiaa.org/doi/abs/10.2514/6.2006-3168},\n\tdoi = {10.2514/6.2006-3168},\n\tabstract = {A hybrid computational fluid dynamics procedure for sonic boom prediction is presented. The method begins with either Euler or Navier-Stokes unstructured mesh computations with mesh refinement adaptation performed to efficiently resolve the solution to a high degree of resolution in the extreme-near-field of the aircraft Flow field data is extracted from the unstructured mesh solution along a cylinder existing within the adapted region. This data is used as boundary conditions for an Euler structured mesh computation to resolve the pressure field several body lengths away from the aircraft The method leverages advantages of both unstructured and structured meshes while avoiding many of their disadvantages. Near-field pressure measurements predicted using the method are compared to wind tunnel measured pressure data of two NASA shape sonic boom aircraft models. Comparisons to Shaped Sonic Boom Demonstrator flight test data are also presented. Results indicate that the method can confidently be used for sonic boom predictions.},\n\tpublisher = {AIAA Paper 2006-3168},\n\tauthor = {Laflin, Kelly R. and Klausmeyer, Steven M. and Chaffin, Mark},\n\tyear = {2006},\n\tpages = {954--965},\n}\n\n\n\n
\n
\n\n\n
\n A hybrid computational fluid dynamics procedure for sonic boom prediction is presented. The method begins with either Euler or Navier-Stokes unstructured mesh computations with mesh refinement adaptation performed to efficiently resolve the solution to a high degree of resolution in the extreme-near-field of the aircraft Flow field data is extracted from the unstructured mesh solution along a cylinder existing within the adapted region. This data is used as boundary conditions for an Euler structured mesh computation to resolve the pressure field several body lengths away from the aircraft The method leverages advantages of both unstructured and structured meshes while avoiding many of their disadvantages. Near-field pressure measurements predicted using the method are compared to wind tunnel measured pressure data of two NASA shape sonic boom aircraft models. Comparisons to Shaped Sonic Boom Demonstrator flight test data are also presented. Results indicate that the method can confidently be used for sonic boom predictions.\n
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\n
\n  \n 2005\n \n \n (10)\n \n \n
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\n \n \n
\n \n\n \n \n Mathelin, L.; Hussaini, Y.; and Zang, T.\n\n\n \n \n \n \n Stochastic approaches to uncertainty quantification in CFD simulations.\n \n \n \n\n\n \n\n\n\n Numerical Algorithms, 38: 209–236. March 2005.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{mathelin2005,\n\ttitle = {Stochastic approaches to uncertainty quantification in\nCFD simulations},\n\tvolume = {38},\n\tdoi = {https://doi.org/10.1007/BF02810624},\n\tjournal = {Numerical Algorithms},\n\tauthor = {Mathelin, Lionel and Hussaini, Yousuff and Zang, Thomas},\n\tmonth = mar,\n\tyear = {2005},\n\tpages = {209--236},\n}\n\n\n\n
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\n \n\n \n \n Bityurin, V.; Bocharov, A.; and Lineberry, J.\n\n\n \n \n \n \n MHD Flow Control in Hypersonic Flight.\n \n \n \n\n\n \n\n\n\n In AIAA/CIRA 13th International Space Planes and Hypersonics Systems and Technologies Conference, 2005. AIAA Paper 2005-3225\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{bityurin2005,\n\ttitle = {{MHD} {Flow} {Control} in {Hypersonic} {Flight}},\n\turldate = {2024-04-30},\n\tbooktitle = {{AIAA}/{CIRA} 13th {International} {Space} {Planes} and {Hypersonics} {Systems} and {Technologies} {Conference}},\n\tpublisher = {AIAA Paper 2005-3225},\n\tauthor = {Bityurin, Valentine and Bocharov, Alexei and Lineberry, John},\n\tyear = {2005},\n}\n\n\n\n\n\n\n\n
\n
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\n \n\n \n \n Hershkowitz, N.\n\n\n \n \n \n \n \n Sheaths: More complicated than you think.\n \n \n \n \n\n\n \n\n\n\n Physics of Plasmas, 12(5): 055502. May 2005.\n \n\n\n\n
\n\n\n\n \n \n \"Sheaths:Paper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{hershkowitz2005,\n\ttitle = {Sheaths: {More} complicated than you think},\n\tvolume = {12},\n\tissn = {1070-664X, 1089-7674},\n\tshorttitle = {Sheaths},\n\turl = {https://pubs.aip.org/pop/article/12/5/055502/1015583/Sheaths-More-complicated-than-you-thinka},\n\tdoi = {10.1063/1.1887189},\n\tabstract = {Sheaths in low temperature collisionless and weakly collisional plasmas are often viewed as simple examples of nonlinear physics. How well do we understand them? Closer examination indicates that they are far from simple. Moreover, many predicted sheath properties have not been experimentally verified and even the appropriate “Bohm velocity” for often encountered two-ion species plasma is unknown. In addition, a variety of sheathlike structures, e.g., double layers, can exist, and many two- and three-dimensional sheath effects have not been considered. Experimental studies of sheaths and presheaths in weakly collisional plasmas are described. A key diagnostic is emissive probes operated in the “limit of zero emission.” Emissive probes provide a sensitive diagnostic of plasma potential with a resolution approaching 0.1V and a spatial resolution of 0.1cm. Combined with planar Langmuir probes and laser-induced fluorescence, they have been used to investigate a wide variety of sheath, presheath, and sheathlike structures. Our experiments have provided some answers but have also raised more questions.},\n\tlanguage = {en},\n\tnumber = {5},\n\turldate = {2024-04-12},\n\tjournal = {Physics of Plasmas},\n\tauthor = {Hershkowitz, Noah},\n\tmonth = may,\n\tyear = {2005},\n\tpages = {055502},\n}\n\n\n\n
\n
\n\n\n
\n Sheaths in low temperature collisionless and weakly collisional plasmas are often viewed as simple examples of nonlinear physics. How well do we understand them? Closer examination indicates that they are far from simple. Moreover, many predicted sheath properties have not been experimentally verified and even the appropriate “Bohm velocity” for often encountered two-ion species plasma is unknown. In addition, a variety of sheathlike structures, e.g., double layers, can exist, and many two- and three-dimensional sheath effects have not been considered. Experimental studies of sheaths and presheaths in weakly collisional plasmas are described. A key diagnostic is emissive probes operated in the “limit of zero emission.” Emissive probes provide a sensitive diagnostic of plasma potential with a resolution approaching 0.1V and a spatial resolution of 0.1cm. Combined with planar Langmuir probes and laser-induced fluorescence, they have been used to investigate a wide variety of sheath, presheath, and sheathlike structures. Our experiments have provided some answers but have also raised more questions.\n
\n\n\n
\n\n\n
\n \n\n \n \n Herdrich, G.; Fertig, M.; Löhle, S.; Pidan, S.; Auweter-Kurtz, M.; and Laux, T.\n\n\n \n \n \n \n \n Oxidation Behavior of Siliconcarbide-Based Materials by Using New Probe Techniques.\n \n \n \n \n\n\n \n\n\n\n Journal of Spacecraft and Rockets, 42(5): 817–824. September 2005.\n \n\n\n\n
\n\n\n\n \n \n \"OxidationPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{herdrich_oxidation_2005,\n\ttitle = {Oxidation {Behavior} of {Siliconcarbide}-{Based} {Materials} by {Using} {New} {Probe} {Techniques}},\n\tvolume = {42},\n\tissn = {0022-4650, 1533-6794},\n\turl = {https://arc.aiaa.org/doi/10.2514/1.12265},\n\tdoi = {10.2514/1.12265},\n\tlanguage = {en},\n\tnumber = {5},\n\turldate = {2023-10-26},\n\tjournal = {Journal of Spacecraft and Rockets},\n\tauthor = {Herdrich, G. and Fertig, M. and Löhle, S. and Pidan, S. and Auweter-Kurtz, M. and Laux, T.},\n\tmonth = sep,\n\tyear = {2005},\n\tpages = {817--824},\n}\n\n\n\n
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\n \n\n \n \n M Hagelaar, G J; and Pitchford, L C\n\n\n \n \n \n \n Solving the Boltzmann equation to obtain electron transport coefficients and rate coefficients for fluid models.\n \n \n \n\n\n \n\n\n\n Plasma Sources Science and Technology, 14(4): 722–722. 2005.\n Publisher: IOP Publishing\n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{mhagelaar2005,\n\ttitle = {Solving the {Boltzmann} equation to obtain electron transport coefficients and rate coefficients for fluid models},\n\tvolume = {14},\n\tdoi = {10.1088/0963-0252/14/4/011},\n\tabstract = {Fluid models of gas discharges require the input of transport coefficients and rate coefficients that depend on the electron energy distribution function. Such coefficients are usually calculated from collision cross-section data by solving the electron Boltzmann equation (BE). In this paper we present a new user-friendly BE solver developed especially for this purpose, freely available under the name BOLSIG+, which is more general and easier to use than most other BE solvers available. The solver provides steady-state solutions of the BE for electrons in a uniform electric field, using the classical two-term expansion, and is able to account for different growth models, quasi-stationary and oscillating fields, electron-neutral collisions and electron-electron collisions. We show that for the approximations we use, the BE takes the form of a convection-diffusion continuity-equation with a non-local source term in energy space. To solve this equation we use an exponential scheme commonly used for convection-diffusion problems. The calculated electron transport coefficients and rate coefficients are defined so as to ensure maximum consistency with the fluid equations. We discuss how these coefficients are best used in fluid models and illustrate the influence of some essential parameters and approximations. © 2005 IOP Publishing Ltd.},\n\tnumber = {4},\n\tjournal = {Plasma Sources Science and Technology},\n\tauthor = {M Hagelaar, G J and Pitchford, L C},\n\tyear = {2005},\n\tnote = {Publisher: IOP Publishing},\n\tpages = {722--722},\n}\n\n\n\n
\n
\n\n\n
\n Fluid models of gas discharges require the input of transport coefficients and rate coefficients that depend on the electron energy distribution function. Such coefficients are usually calculated from collision cross-section data by solving the electron Boltzmann equation (BE). In this paper we present a new user-friendly BE solver developed especially for this purpose, freely available under the name BOLSIG+, which is more general and easier to use than most other BE solvers available. The solver provides steady-state solutions of the BE for electrons in a uniform electric field, using the classical two-term expansion, and is able to account for different growth models, quasi-stationary and oscillating fields, electron-neutral collisions and electron-electron collisions. We show that for the approximations we use, the BE takes the form of a convection-diffusion continuity-equation with a non-local source term in energy space. To solve this equation we use an exponential scheme commonly used for convection-diffusion problems. The calculated electron transport coefficients and rate coefficients are defined so as to ensure maximum consistency with the fluid equations. We discuss how these coefficients are best used in fluid models and illustrate the influence of some essential parameters and approximations. © 2005 IOP Publishing Ltd.\n
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\n \n\n \n \n Wright, M. J; Bose, D; Palmer, G. E; and Levin, E\n\n\n \n \n \n \n Recommended Collision Integrals for Transport Property Computations, Part 1: Air Species.\n \n \n \n\n\n \n\n\n\n AIAA Journal, 43(12): 2558–2564. 2005.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{wright2005,\n\ttitle = {Recommended {Collision} {Integrals} for {Transport} {Property} {Computations}, {Part} 1: {Air} {Species}},\n\tvolume = {43},\n\tnumber = {12},\n\tjournal = {AIAA Journal},\n\tauthor = {Wright, Michael J and Bose, D and Palmer, Grant E and Levin, E},\n\tyear = {2005},\n\tpages = {2558--2564},\n}\n\n\n\n
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\n \n\n \n \n Druguet, M.; Candler, G. V; and Nompelis, I.\n\n\n \n \n \n \n Effect of Numerics on Navier–Stokes Computations of Hypersonic Double-Cone Flows.\n \n \n \n\n\n \n\n\n\n AIAA Journal, 43(5). 2005.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{druguet2005,\n\ttitle = {Effect of {Numerics} on {Navier}--{Stokes} {Computations} of {Hypersonic} {Double}-{Cone} {Flows}},\n\tvolume = {43},\n\tnumber = {5},\n\tjournal = {AIAA Journal},\n\tauthor = {Druguet, Marie-Claude and Candler, Graham V and Nompelis, Ioannis},\n\tyear = {2005},\n}\n\n\n\n
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\n \n\n \n \n Gosse, R.; and Candler, G. V\n\n\n \n \n \n \n Diffusion Flux Modeling: Application to Direct Entry Problems.\n \n \n \n\n\n \n\n\n\n In Reno, NV, January 2005. \\AIAA Paper\\ 2005-389\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{gosse2005,\n\taddress = {Reno, NV},\n\ttitle = {Diffusion {Flux} {Modeling}: {Application} to {Direct} {Entry} {Problems}},\n\tpublisher = {\\{AIAA Paper\\} 2005-389},\n\tauthor = {Gosse, Ryan and Candler, Graham V},\n\tmonth = jan,\n\tyear = {2005},\n}\n\n\n\n
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\n \n\n \n \n Mani, A.; Wang, M.; and Moin, P.\n\n\n \n \n \n \n Computational Study of Aero-Optical Distortion by Turbulent Wake.\n \n \n \n\n\n \n\n\n\n In Toronto, Ontario Canada, June 2005. \\AIAA Paper\\ 2005-4655\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{mani2005,\n\taddress = {Toronto, Ontario Canada},\n\ttitle = {Computational {Study} of {Aero}-{Optical} {Distortion} by {Turbulent} {Wake}},\n\tdoi = {10.2514/6.2005-4655},\n\tpublisher = {\\{AIAA Paper\\} 2005-4655},\n\tauthor = {Mani, Ali and Wang, Meng and Moin, Parviz},\n\tmonth = jun,\n\tyear = {2005},\n}\n\n\n\n
\n
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\n \n\n \n \n Lips, T.; and Fritsche, B.\n\n\n \n \n \n \n A comparison of commonly used re-entry analysis tools.\n \n \n \n\n\n \n\n\n\n In volume 57, pages 312–323, July 2005. Pergamon\n Issue: 2-8\n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@inproceedings{lips2005,\n\ttitle = {A comparison of commonly used re-entry analysis tools},\n\tvolume = {57},\n\tdoi = {10.1016/j.actaastro.2005.03.010},\n\tabstract = {Most spacecraft or rocket bodies re-entering the Earth's atmosphere, controlled or uncontrolled, do not demise completely during re-entry. Fragments of these re-entry objects survive and reach the ground where they pose a risk to people. Re-entry tools have been developed all over the world in order to calculate the destruction processes and to assess the resulting ground risk. This paper describes the NASA re-entry analysis tools DAS (Debris Assessment Software) and ORSAT (Object Re-entry Survival Analysis Tool), and the ESA tools SCARAB (Spacecraft Atmospheric Re-entry and Aero-thermal Breakup) and SESAM (Spacecraft Entry Survival Analysis Module). Results calculated with these tools are compared in order to identify the major differences. Final recommendations are given in order to improve these tools and to minimize the identified differences. © 2005 Elsevier Ltd. All rights reserved.},\n\tpublisher = {Pergamon},\n\tauthor = {Lips, Tobias and Fritsche, Bent},\n\tmonth = jul,\n\tyear = {2005},\n\tnote = {Issue: 2-8},\n\tkeywords = {Re-entry, Risk analysis, Space debris},\n\tpages = {312--323},\n}\n\n\n\n
\n
\n\n\n
\n Most spacecraft or rocket bodies re-entering the Earth's atmosphere, controlled or uncontrolled, do not demise completely during re-entry. Fragments of these re-entry objects survive and reach the ground where they pose a risk to people. Re-entry tools have been developed all over the world in order to calculate the destruction processes and to assess the resulting ground risk. This paper describes the NASA re-entry analysis tools DAS (Debris Assessment Software) and ORSAT (Object Re-entry Survival Analysis Tool), and the ESA tools SCARAB (Spacecraft Atmospheric Re-entry and Aero-thermal Breakup) and SESAM (Spacecraft Entry Survival Analysis Module). Results calculated with these tools are compared in order to identify the major differences. Final recommendations are given in order to improve these tools and to minimize the identified differences. © 2005 Elsevier Ltd. All rights reserved.\n
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\n  \n 2004\n \n \n (12)\n \n \n
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\n \n\n \n \n Schneider, S. P.\n\n\n \n \n \n \n Hypersonic laminar–turbulent transition on circular cones and scramjet forebodies.\n \n \n \n\n\n \n\n\n\n Progress in Aerospace Sciences, 40(1): 1–50. February 2004.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{schneider2004,\n\ttitle = {Hypersonic laminar–turbulent transition on circular cones and scramjet forebodies},\n\tvolume = {40},\n\tdoi = {10.1016/j.paerosci.2003.11.001},\n\tabstract = {Laminar–turbulent transition in hypersonic boundary layers has a dramatic effect on heat transfer, skin friction, and separation. This effect is critical to reentry vehicles and airbreathing cruise vehicles, yet the physics of the transition process is not yet well enough understood to be used for predictive purposes. The literature for transition on circular cones and scramjet forebodies is reviewed, from an experimental point of view. Ground experiments, emphasized here, nearly always suffer from ambiguity caused by operating in the presence of high levels of facility noise. Measurements of the instabilities leading to transition reduce much of this ambiguity, and thus these instability measurements are emphasized. A number of transition measurements have also provided good control of extraneous effects, and several of these measurements are compared in detail. Small bluntness always delays transition on smooth cones at zero angle of attack (AOA), while large bluntness creates a change in mechanism that again moves transition forwards. For smooth cones at AOA with small or negligible bluntness, transition is always leeside-forward and windside-aft, although the movement with AOA is tunnel and geometry dependent. For cones with large bluntness, transition becomes windside forward and leeside aft. In both cases, nosetip roughness may be involved in the trend reversal. Reliable prediction of the trend reversal conditions is one of many topics requiring additional research. The limited existing database for transition on scramjet-vehicle forebodies is also reviewed, along with the literature for transition in the compression corners that are often a part of such forebody designs.},\n\tnumber = {1},\n\turldate = {2024-12-30},\n\tjournal = {Progress in Aerospace Sciences},\n\tauthor = {Schneider, Steven P.},\n\tmonth = feb,\n\tyear = {2004},\n\tpages = {1--50},\n}\n\n\n\n\n\n\n\n
\n
\n\n\n
\n Laminar–turbulent transition in hypersonic boundary layers has a dramatic effect on heat transfer, skin friction, and separation. This effect is critical to reentry vehicles and airbreathing cruise vehicles, yet the physics of the transition process is not yet well enough understood to be used for predictive purposes. The literature for transition on circular cones and scramjet forebodies is reviewed, from an experimental point of view. Ground experiments, emphasized here, nearly always suffer from ambiguity caused by operating in the presence of high levels of facility noise. Measurements of the instabilities leading to transition reduce much of this ambiguity, and thus these instability measurements are emphasized. A number of transition measurements have also provided good control of extraneous effects, and several of these measurements are compared in detail. Small bluntness always delays transition on smooth cones at zero angle of attack (AOA), while large bluntness creates a change in mechanism that again moves transition forwards. For smooth cones at AOA with small or negligible bluntness, transition is always leeside-forward and windside-aft, although the movement with AOA is tunnel and geometry dependent. For cones with large bluntness, transition becomes windside forward and leeside aft. In both cases, nosetip roughness may be involved in the trend reversal. Reliable prediction of the trend reversal conditions is one of many topics requiring additional research. The limited existing database for transition on scramjet-vehicle forebodies is also reviewed, along with the literature for transition in the compression corners that are often a part of such forebody designs.\n
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\n \n\n \n \n Nompelis, I.\n\n\n \n \n \n \n \n Computational study of hypersonic double -cone experiments for code validation.\n \n \n \n \n\n\n \n\n\n\n Ph.D. Thesis, University of Minnesota, 2004.\n \n\n\n\n
\n\n\n\n \n \n \"ComputationalPaper\n  \n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@phdthesis{nompelis2004,\n\ttitle = {Computational study of hypersonic double -cone experiments for code validation},\n\turl = {https://www.proquest.com/dissertations-theses/computational-study-hypersonic-double-cone/docview/305157073},\n\tschool = {University of Minnesota},\n\tauthor = {Nompelis, Ioannis},\n\tyear = {2004},\n}\n\n\n\n
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\n \n\n \n \n Faragher, J.\n\n\n \n \n \n \n Probabilistic Methods for the Quantification of Uncertainty and Error in Computational Fluid Dynamics Simulations.\n \n \n \n\n\n \n\n\n\n Technical Report DSTO-TR-1633, Australian Government Department of Defense, October 2004.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@techreport{faragher2004,\n\ttitle = {Probabilistic {Methods} for the {Quantification} of {Uncertainty} and {Error} in {Computational} {Fluid} {Dynamics} {Simulations}},\n\tnumber = {DSTO-TR-1633},\n\tinstitution = {Australian Government Department of Defense},\n\tauthor = {Faragher, John},\n\tmonth = oct,\n\tyear = {2004},\n}\n\n\n\n
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\n \n\n \n \n Gnoffo, P.; and White, J.\n\n\n \n \n \n \n Computational Aerothermodynamic Simulation Issues on Unstructured Grids.\n \n \n \n\n\n \n\n\n\n In 37th AIAA Thermophysics Conference, Portland, Oregon, June 2004. American Institute of Aeronautics and Astronautics\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{gnoffo2004,\n\taddress = {Portland, Oregon},\n\ttitle = {Computational {Aerothermodynamic} {Simulation} {Issues} on {Unstructured} {Grids}},\n\tdoi = {10.2514/6.2004-2371},\n\tlanguage = {en},\n\turldate = {2024-05-27},\n\tbooktitle = {37th {AIAA} {Thermophysics} {Conference}},\n\tpublisher = {American Institute of Aeronautics and Astronautics},\n\tauthor = {Gnoffo, Peter and White, Jeffery},\n\tmonth = jun,\n\tyear = {2004},\n}\n\n\n\n\n\n\n\n
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\n \n\n \n \n Magin, T. E.; and Degrez, G.\n\n\n \n \n \n \n Transport algorithms for partially ionized and unmagnetized plasmas.\n \n \n \n\n\n \n\n\n\n Journal of Computational Physics, 198(2): 424–449. August 2004.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{magin2004,\n\ttitle = {Transport algorithms for partially ionized and unmagnetized plasmas},\n\tvolume = {198},\n\tdoi = {10.1016/J.JCP.2004.01.012},\n\tabstract = {A new formalism for the transport properties of partially ionized and unmagnetized plasmas is investigated from a computational point of view. Heavy particle transport expressions for shear viscosity, translational thermal conductivity, and thermal diffusion ratios are obtained from the solution of symmetric linear systems. Electron transport properties are also presented. A general Stefan-Maxwell equation and two approximate formulations deal with diffusion phenomenon. Well-posedness of the transport properties is established, provided that some conditions on the kinetic data are met. The mathematical structure of the transport matrices is readily used to build transport algorithms inspired by Ern and Giovangigli [J. Comput. Phys. 120 (1995) 105]. These algorithms rely either on a direct linear solver or on convergent iterative Krylov projection methods, such as the conjugate gradient. The Stefan-Maxwell matrix is singular and a mass conservation constraint completes the system of equations. A yet symmetric and non-singular Stefan-Maxwell matrix including the mass constraint is introduced for the direct method. A suitable projector associated with the singular form of the matrix is used for the iterative methods. An 11-species air mixture in local thermodynamic equilibrium at atmospheric pressure serves as benchmark to assess the physical model and numerical methods. Superiority of the conjugate gradient method with respect to the direct solver and approximate mixture rules found in the literature is demonstrated in terms of accuracy and computational cost. © 2004 Elsevier Inc. All rights reserved.},\n\tnumber = {2},\n\tjournal = {Journal of Computational Physics},\n\tauthor = {Magin, Thierry E. and Degrez, Gérard},\n\tmonth = aug,\n\tyear = {2004},\n\tkeywords = {Diffusion, Iterative methods, Krylov subspaces, Partially ionized mixtures, Transport coefficients, Unmagnetized plasmas},\n\tpages = {424--449},\n}\n\n\n\n
\n
\n\n\n
\n A new formalism for the transport properties of partially ionized and unmagnetized plasmas is investigated from a computational point of view. Heavy particle transport expressions for shear viscosity, translational thermal conductivity, and thermal diffusion ratios are obtained from the solution of symmetric linear systems. Electron transport properties are also presented. A general Stefan-Maxwell equation and two approximate formulations deal with diffusion phenomenon. Well-posedness of the transport properties is established, provided that some conditions on the kinetic data are met. The mathematical structure of the transport matrices is readily used to build transport algorithms inspired by Ern and Giovangigli [J. Comput. Phys. 120 (1995) 105]. These algorithms rely either on a direct linear solver or on convergent iterative Krylov projection methods, such as the conjugate gradient. The Stefan-Maxwell matrix is singular and a mass conservation constraint completes the system of equations. A yet symmetric and non-singular Stefan-Maxwell matrix including the mass constraint is introduced for the direct method. A suitable projector associated with the singular form of the matrix is used for the iterative methods. An 11-species air mixture in local thermodynamic equilibrium at atmospheric pressure serves as benchmark to assess the physical model and numerical methods. Superiority of the conjugate gradient method with respect to the direct solver and approximate mixture rules found in the literature is demonstrated in terms of accuracy and computational cost. © 2004 Elsevier Inc. All rights reserved.\n
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\n \n\n \n \n Alder, B. J.; and Wainwright, T. E.\n\n\n \n \n \n \n \n Studies in Molecular Dynamics. I. General Method.\n \n \n \n \n\n\n \n\n\n\n The Journal of Chemical Physics, 31(2): 459–459. August 2004.\n Publisher: American Institute of PhysicsAIP\n\n\n\n
\n\n\n\n \n \n \"StudiesPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{alder2004,\n\ttitle = {Studies in {Molecular} {Dynamics}. {I}. {General} {Method}},\n\tvolume = {31},\n\turl = {https://aip.scitation.org/doi/abs/10.1063/1.1730376},\n\tdoi = {10.1063/1.1730376},\n\tabstract = {A method is outlined by which it is possible to calculate exactly the behavior of several hundred interacting classical particles. The study of this many‐body problem is carried out by an electroni...},\n\tnumber = {2},\n\tjournal = {The Journal of Chemical Physics},\n\tauthor = {Alder, B. J. and Wainwright, T. E.},\n\tmonth = aug,\n\tyear = {2004},\n\tnote = {Publisher: American Institute of PhysicsAIP},\n\tpages = {459--459},\n}\n\n\n\n
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\n A method is outlined by which it is possible to calculate exactly the behavior of several hundred interacting classical particles. The study of this many‐body problem is carried out by an electroni...\n
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\n \n\n \n \n Capitelli, M; Colonna, G; and Esposito, F\n\n\n \n \n \n \n On the Coupling of Vibrational Relaxation with the Dissociation-Recombination Kinetics: From Dynamics to Aerospace Applications.\n \n \n \n\n\n \n\n\n\n The Journal of Physical Chemistry A, 108(41): 8930–8934. 2004.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{capitelli2004,\n\ttitle = {On the {Coupling} of {Vibrational} {Relaxation} with the {Dissociation}-{Recombination} {Kinetics}: {From} {Dynamics} to {Aerospace} {Applications}},\n\tvolume = {108},\n\tnumber = {41},\n\tjournal = {The Journal of Physical Chemistry A},\n\tauthor = {Capitelli, M and Colonna, G and Esposito, F},\n\tyear = {2004},\n\tpages = {8930--8934},\n}\n\n\n\n
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\n \n\n \n \n Pade, O.; Frumker, E.; and Rojt, P. I.\n\n\n \n \n \n \n Optical distortions caused by propagation through turbulent shear layers.\n \n \n \n\n\n \n\n\n\n In Gonglewski, J. D; and Stein, K., editor(s), volume 5237, pages 31–38, Barcelona, Spain, February 2004. SPIE\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@inproceedings{pade2004,\n\taddress = {Barcelona, Spain},\n\ttitle = {Optical distortions caused by propagation through turbulent shear layers},\n\tvolume = {5237},\n\tpublisher = {SPIE},\n\tauthor = {Pade, Offer and Frumker, Evgeny and Rojt, Paula Ines},\n\teditor = {Gonglewski, John D and Stein, Karin},\n\tmonth = feb,\n\tyear = {2004},\n\tpages = {31--38},\n}\n\n\n\n
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\n \n\n \n \n Rasmussen, C. E.\n\n\n \n \n \n \n \n Gaussian Processes in Machine Learning.\n \n \n \n \n\n\n \n\n\n\n In Bousquet, O.; von Luxburg, U.; and Rätsch, G., editor(s), Advanced Lectures on Machine Learning: ML Summer Schools 2003, Canberra, Australia, February 2 - 14, 2003, Tübingen, Germany, August 4 - 16, 2003, Revised Lectures, pages 63–71. Springer Berlin Heidelberg, Berlin, Heidelberg, 2004.\n \n\n\n\n
\n\n\n\n \n \n \"GaussianPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@incollection{rasmussen2004,\n\taddress = {Berlin, Heidelberg},\n\ttitle = {Gaussian {Processes} in {Machine} {Learning}},\n\tisbn = {978-3-540-28650-9},\n\turl = {https://doi.org/10.1007/978-3-540-28650-9_4},\n\tabstract = {We give a basic introduction to Gaussian Process regression models. We focus on understanding the role of the stochastic process and how it is used to define a distribution over functions. We present the simple equations for incorporating training data and examine how to learn the hyperparameters using the marginal likelihood. We explain the practical advantages of Gaussian Process and end with conclusions and a look at the current trends in GP work.},\n\tbooktitle = {Advanced {Lectures} on {Machine} {Learning}: {ML} {Summer} {Schools} 2003, {Canberra}, {Australia}, {February} 2 - 14, 2003, {Tübingen}, {Germany}, {August} 4 - 16, 2003, {Revised} {Lectures}},\n\tpublisher = {Springer Berlin Heidelberg},\n\tauthor = {Rasmussen, Carl Edward},\n\teditor = {Bousquet, Olivier and von Luxburg, Ulrike and Rätsch, Gunnar},\n\tyear = {2004},\n\tdoi = {10.1007/978-3-540-28650-9_4},\n\tpages = {63--71},\n}\n\n\n\n
\n
\n\n\n
\n We give a basic introduction to Gaussian Process regression models. We focus on understanding the role of the stochastic process and how it is used to define a distribution over functions. We present the simple equations for incorporating training data and examine how to learn the hyperparameters using the marginal likelihood. We explain the practical advantages of Gaussian Process and end with conclusions and a look at the current trends in GP work.\n
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\n \n\n \n \n Martin, M. P.\n\n\n \n \n \n \n DNS of Hypersonic Turbulent Boundary Layers.\n \n \n \n\n\n \n\n\n\n In 2004. AIAA Paper 2004-2337\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{martin2004,\n\ttitle = {{DNS} of {Hypersonic} {Turbulent} {Boundary} {Layers}},\n\tdoi = {10.2514/6.2004-2337},\n\tabstract = {We present a direct numerical simulation database of supersonic and hypersonic turbu- lent boundary layers. The systematic procedure for initializing the turbulent flow fields at controlled Mach number and Reynolds number conditions is described. It is shown that simulation transients are less than 10\\% of the time required for gathering statistical data of the turbulent flows. The experimental conditions of Debiffeve1,2 and Elena 3,4 are sim- ulated. The magnitude of velocity and temperature fiuctuations, as well as the turbulent shear stresses given by the direct numerical simulations are in excellent agreement with the experimental data. Using the direct numerical simulation database we perform paramet- ric studies varying freestream Mach number in the range of 3 to 8 and wall-temperature condition for wall-to-freestream-temperature ratio of 2 to 5.5. © 2004 by the American Institute of Aeronautics and Astronautics, Inc.},\n\tpublisher = {AIAA Paper 2004-2337},\n\tauthor = {Martin, M. Pino},\n\tyear = {2004},\n}\n\n\n\n
\n
\n\n\n
\n We present a direct numerical simulation database of supersonic and hypersonic turbu- lent boundary layers. The systematic procedure for initializing the turbulent flow fields at controlled Mach number and Reynolds number conditions is described. It is shown that simulation transients are less than 10% of the time required for gathering statistical data of the turbulent flows. The experimental conditions of Debiffeve1,2 and Elena 3,4 are sim- ulated. The magnitude of velocity and temperature fiuctuations, as well as the turbulent shear stresses given by the direct numerical simulations are in excellent agreement with the experimental data. Using the direct numerical simulation database we perform paramet- ric studies varying freestream Mach number in the range of 3 to 8 and wall-temperature condition for wall-to-freestream-temperature ratio of 2 to 5.5. © 2004 by the American Institute of Aeronautics and Astronautics, Inc.\n
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\n \n\n \n \n Marrone, P. V.; and Treanor, C. E.\n\n\n \n \n \n \n Chemical Relaxation with Preferential Dissociation from Excited Vibrational Levels.\n \n \n \n\n\n \n\n\n\n The Physics of Fluids, 6(9). 2004.\n Publisher: American Institute of PhysicsAIP\n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{marrone2004,\n\ttitle = {Chemical {Relaxation} with {Preferential} {Dissociation} from {Excited} {Vibrational} {Levels}},\n\tvolume = {6},\n\tdoi = {10.1063/1.1706888},\n\tabstract = {The rate of molecular dissociation behind strong shock waves is calculated with the assumption that dissociation can occur preferentially from the higher vibrational levels. An exponential probabil...},\n\tnumber = {9},\n\tjournal = {The Physics of Fluids},\n\tauthor = {Marrone, Paul V. and Treanor, Charles E.},\n\tyear = {2004},\n\tnote = {Publisher: American Institute of PhysicsAIP},\n}\n\n\n\n
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\n The rate of molecular dissociation behind strong shock waves is calculated with the assumption that dissociation can occur preferentially from the higher vibrational levels. An exponential probabil...\n
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\n \n\n \n \n Plemmons, D.; Feather, B.; Baxter, L.; Wilson, R.; and Jumper, E.\n\n\n \n \n \n \n Aero-optics effects testing in AEDC wind tunnels.\n \n \n \n\n\n \n\n\n\n In 2004. \n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@inproceedings{plemmons2004,\n\ttitle = {Aero-optics effects testing in {AEDC} wind tunnels},\n\tisbn = {978-1-62410-026-0},\n\tdoi = {10.2514/6.2004-2499},\n\tabstract = {Aerodynamic flows around aircraft structures induce density variations in the boundarylayer flows and slipstream. The interaction of these density variations with a laser beam (aero-optics) can severely alter the beam characteristics, making it difficult or impossible to focus laser power on distant objects or transmit laser communications signals from a flight vehicle. Successful development of airborne laser weapons or communications systems will entail the development of adaptive optic or aerodynamic solutions to the corrupting effects of aero-optics. Extensive wind tunnel testing will be required to develop and validate the solutions. The Arnold Engineering Development Center (AEDC) houses wind tunnel facilities that will probably be required for aero-optics testing of large-scale airborne laser systems. AEDC's wind tunnel facilities are complemented by advanced modeling and simulation capabilities. This paper presents an overview of these complementary capabilities as they are applicable to past and future aero-optics testing at AEDC.},\n\tauthor = {Plemmons, David and Feather, Brian and Baxter, Lance and Wilson, Robert and Jumper, Eric},\n\tyear = {2004},\n}\n\n\n\n
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\n Aerodynamic flows around aircraft structures induce density variations in the boundarylayer flows and slipstream. The interaction of these density variations with a laser beam (aero-optics) can severely alter the beam characteristics, making it difficult or impossible to focus laser power on distant objects or transmit laser communications signals from a flight vehicle. Successful development of airborne laser weapons or communications systems will entail the development of adaptive optic or aerodynamic solutions to the corrupting effects of aero-optics. Extensive wind tunnel testing will be required to develop and validate the solutions. The Arnold Engineering Development Center (AEDC) houses wind tunnel facilities that will probably be required for aero-optics testing of large-scale airborne laser systems. AEDC's wind tunnel facilities are complemented by advanced modeling and simulation capabilities. This paper presents an overview of these complementary capabilities as they are applicable to past and future aero-optics testing at AEDC.\n
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\n  \n 2003\n \n \n (15)\n \n \n
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\n \n\n \n \n Lucor, D; Xiu, D; Su, C; and Karniadakis, G\n\n\n \n \n \n \n Predictability and Uncertainty in CFD.\n \n \n \n\n\n \n\n\n\n International Journal for Numerical Methods in Fluids, 43(5): 463–596. October 2003.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@article{lucor2003,\n\ttitle = {Predictability and {Uncertainty} in {CFD}},\n\tvolume = {43},\n\tdoi = {https://doi.org/10.1002/fld.500},\n\tnumber = {5},\n\tjournal = {International Journal for Numerical Methods in Fluids},\n\tauthor = {Lucor, D and Xiu, D and Su, C and Karniadakis, G},\n\tmonth = oct,\n\tyear = {2003},\n\tpages = {463--596},\n}\n\n\n\n
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\n \n\n \n \n Lucor, D.; Xiu, D.; Su, C.; and Karniadakis, G.\n\n\n \n \n \n \n \n Predictability and Uncertainty in CFD.\n \n \n \n \n\n\n \n\n\n\n International Journal for Numerical Methods in Fluids, (43): 483–505. 2003.\n \n\n\n\n
\n\n\n\n \n \n \"PredictabilityPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@article{lucor2003,\n\ttitle = {Predictability and {Uncertainty} in {CFD}},\n\turl = {https://onlinelibrary.wiley.com/doi/epdf/10.1002/fld.500},\n\tdoi = {10.1002/fld.500},\n\tnumber = {43},\n\tjournal = {International Journal for Numerical Methods in Fluids},\n\tauthor = {Lucor, D. and Xiu, D. and Su, C.-H. and Karniadakis, G.},\n\tyear = {2003},\n\tpages = {483--505},\n}\n\n\n\n
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\n \n\n \n \n Staehler, J. M.; Mall, S.; and Zawada, L. P.\n\n\n \n \n \n \n Frequency dependence of high-cycle fatigue behavior of CVI C/SiC at room temperature.\n \n \n \n\n\n \n\n\n\n Composites Science and Technology, 63(15): 2121–2131. November 2003.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n\n\n\n
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@article{staehler_frequency_2003,\n\ttitle = {Frequency dependence of high-cycle fatigue behavior of {CVI} {C}/{SiC} at room temperature},\n\tvolume = {63},\n\tissn = {0266-3538},\n\tdoi = {10.1016/S0266-3538(03)00190-8},\n\tabstract = {Effects of loading frequency on high-cycle fatigue behavior of a chemical vapor infiltrated carbon fiber reinforced silicon carbide composite were investigated. Tension–tension fatigue tests were conducted at three frequencies, 4, 40 and 375 Hz. Fatigue run out was set to 107 cycles. Applied stress versus cycles to failure (S–N) relationships were developed for these three frequencies. At 4 and 40 Hz, fatigue run out was achieved at a stress level of 375 MPa. At 375 Hz, stress level for run out was 350 MPa. Frequency dependence was observed between the two lower frequencies (4 and 40 Hz) and the higher frequency (375 Hz), but not between two lower frequencies (4 and 40 Hz). This manifested as a reduction in cycles to failure at 375 Hz compared to 4 and 40 Hz at a given stress level. Specimen surface temperature increased due to internal heat generation from sliding friction between constituents of the composite under cyclic loading. This increase was directly related to frequency and/or applied cyclic stress level. There was no clear indication that frequency greatly impacted either the stress-strain response or the overall appearance of fracture surfaces. However, a closer examination of specimens cycled at the highest frequency (375 Hz) showed evidence of the localized oxidation at fiber surfaces that might have attributed to the reduction in fatigue life at this frequency.},\n\tnumber = {15},\n\turldate = {2023-10-30},\n\tjournal = {Composites Science and Technology},\n\tauthor = {Staehler, James M. and Mall, Shankar and Zawada, Larry P.},\n\tmonth = nov,\n\tyear = {2003},\n\tkeywords = {A. Ceramics-matrix composites, B. Fatigue, High-cycle fatigue},\n\tpages = {2121--2131},\n}\n\n\n\n
\n
\n\n\n
\n Effects of loading frequency on high-cycle fatigue behavior of a chemical vapor infiltrated carbon fiber reinforced silicon carbide composite were investigated. Tension–tension fatigue tests were conducted at three frequencies, 4, 40 and 375 Hz. Fatigue run out was set to 107 cycles. Applied stress versus cycles to failure (S–N) relationships were developed for these three frequencies. At 4 and 40 Hz, fatigue run out was achieved at a stress level of 375 MPa. At 375 Hz, stress level for run out was 350 MPa. Frequency dependence was observed between the two lower frequencies (4 and 40 Hz) and the higher frequency (375 Hz), but not between two lower frequencies (4 and 40 Hz). This manifested as a reduction in cycles to failure at 375 Hz compared to 4 and 40 Hz at a given stress level. Specimen surface temperature increased due to internal heat generation from sliding friction between constituents of the composite under cyclic loading. This increase was directly related to frequency and/or applied cyclic stress level. There was no clear indication that frequency greatly impacted either the stress-strain response or the overall appearance of fracture surfaces. However, a closer examination of specimens cycled at the highest frequency (375 Hz) showed evidence of the localized oxidation at fiber surfaces that might have attributed to the reduction in fatigue life at this frequency.\n
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\n \n\n \n \n Chen, L. J.; Liaw, P. K.; McDaniels, R. L.; and Klarstrom, D. L.\n\n\n \n \n \n \n The low-cycle fatigue and fatigue-crack-growth behavior of HAYNES® HR-120 alloy.\n \n \n \n\n\n \n\n\n\n Metallurgical and Materials Transactions A, 34(7): 1451–1460. July 2003.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{chen_low-cycle_2003,\n\ttitle = {The low-cycle fatigue and fatigue-crack-growth behavior of {HAYNES}® {HR}-120 alloy},\n\tvolume = {34},\n\tissn = {1543-1940},\n\tdoi = {10.1007/s11661-003-0257-z},\n\tabstract = {The low-cycle fatigue and fatigue-crack-growth behavior of the HAYNES HR-120 alloy was investigated over the temperature range of 24°C to 980°C in laboratory air. The result showed that increasing the temperature usually led to a substantial decrease in the low-cycle fatigue life. The reduction of fatigue life could be attributed to oxidation and dynamic strain-aging (DSA) processes. The strain vs fatigue-life data obtained at different temperatures were analyzed. It was also found that the fatigue-crack-growth rate per cycle generally increased with increasing temperature and R ratio (R=σmin/σmax, where σmin and σmax are the applied minimum and maximum stresses, respectively). The relationship between the stress-intensity-factor range and fatigue-crack-growth rate was determined. Scanning-electron-microscopy (SEM) examinations of the fracture surfaces revealed that the fatigue cracks initiated and propagated predominantly in a transgranular mode.},\n\tlanguage = {en},\n\tnumber = {7},\n\turldate = {2023-10-23},\n\tjournal = {Metallurgical and Materials Transactions A},\n\tauthor = {Chen, L. J. and Liaw, P. K. and McDaniels, R. L. and Klarstrom, D. L.},\n\tmonth = jul,\n\tyear = {2003},\n\tkeywords = {Cyclic Deformation, Fatigue, Fatigue Life, Material Transaction, Serrate Flow},\n\tpages = {1451--1460},\n}\n\n\n\n\n\n\n\n\n\n\n\n
\n
\n\n\n
\n The low-cycle fatigue and fatigue-crack-growth behavior of the HAYNES HR-120 alloy was investigated over the temperature range of 24°C to 980°C in laboratory air. The result showed that increasing the temperature usually led to a substantial decrease in the low-cycle fatigue life. The reduction of fatigue life could be attributed to oxidation and dynamic strain-aging (DSA) processes. The strain vs fatigue-life data obtained at different temperatures were analyzed. It was also found that the fatigue-crack-growth rate per cycle generally increased with increasing temperature and R ratio (R=σmin/σmax, where σmin and σmax are the applied minimum and maximum stresses, respectively). The relationship between the stress-intensity-factor range and fatigue-crack-growth rate was determined. Scanning-electron-microscopy (SEM) examinations of the fracture surfaces revealed that the fatigue cracks initiated and propagated predominantly in a transgranular mode.\n
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\n \n\n \n \n Malik, M. R.\n\n\n \n \n \n \n \n Hypersonic Flight Transition Data Analysis Using Parabolized Stability Equations with Chemistry Effects.\n \n \n \n \n\n\n \n\n\n\n Journal of Spacecraft and Rockets, 40(3): 332–344. 2003.\n \n\n\n\n
\n\n\n\n \n \n \"HypersonicPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{malik2003,\n\ttitle = {Hypersonic {Flight} {Transition} {Data} {Analysis} {Using} {Parabolized} {Stability} {Equations} with {Chemistry} {Effects}},\n\tvolume = {40},\n\tissn = {0022-4650},\n\turl = {https://doi.org/10.2514/2.3968},\n\tdoi = {10.2514/2.3968},\n\tnumber = {3},\n\turldate = {2023-08-08},\n\tjournal = {Journal of Spacecraft and Rockets},\n\tauthor = {Malik, Mujeeb R.},\n\tyear = {2003},\n\tpages = {332--344},\n}\n\n\n\n\n\n\n\n\n\n\n\n
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\n \n\n \n \n Ghatee, M H; and Sanchooli, M\n\n\n \n \n \n \n \n Viscosity and thermal conductivity of cesium vapor at high temperatures.\n \n \n \n \n\n\n \n\n\n\n Fluid Phase Equilibria, 214(2): 197–209. 2003.\n \n\n\n\n
\n\n\n\n \n \n \"ViscosityPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{ghatee2003,\n\ttitle = {Viscosity and thermal conductivity of cesium vapor at high temperatures},\n\tvolume = {214},\n\turl = {http://www.sciencedirect.com/science/article/pii/S0378381203003522},\n\tdoi = {10.1016/S0378-3812(03)00352-2},\n\tabstract = {This paper presents the prediction of equilibrium thermodynamic properties of liquid cesium metal and transport properties of cesium metal vapor by applying an identical potential function obtained from liquid cohesive energy density data including data for the supercooled state at proximity of absolute zero. Prediction of equilibrium thermodynamic properties is made possible by derivation of isotherms, which is accurately linear in the whole liquid range including metal--nonmetal transition. For transport properties, the collision integrals are tabulated, and values of viscosity plus thermal conductivity of cesium vapor are obtained from Chapman--Enskog solutions of Boltzman equation. The viscosity values are in agreement with experiment within \\${\\textbackslash}pm\\$4\\% with average deviation 2\\%, and are in agreement with theory within \\${\\textbackslash}pm\\$4.70\\% with average deviation 3.26\\%. The thermal conductivity values are in agreement with experiment within 11\\% with average deviation 8\\%, and are in agreement with theory within 4.2\\% with average deviation 2.8\\% over the temperature range considered. It is likely that the potential function can be used to predict both equilibrium and transport properties with reasonably good accuracies.},\n\tnumber = {2},\n\tjournal = {Fluid Phase Equilibria},\n\tauthor = {Ghatee, M H and Sanchooli, M},\n\tyear = {2003},\n\tkeywords = {Cohesive energy density, Equation of state, Liquid cesium metal, Potential function, Thermal conductivity, Viscosity coefficient},\n\tpages = {197--209},\n}\n\n\n\n
\n
\n\n\n
\n This paper presents the prediction of equilibrium thermodynamic properties of liquid cesium metal and transport properties of cesium metal vapor by applying an identical potential function obtained from liquid cohesive energy density data including data for the supercooled state at proximity of absolute zero. Prediction of equilibrium thermodynamic properties is made possible by derivation of isotherms, which is accurately linear in the whole liquid range including metal–nonmetal transition. For transport properties, the collision integrals are tabulated, and values of viscosity plus thermal conductivity of cesium vapor are obtained from Chapman–Enskog solutions of Boltzman equation. The viscosity values are in agreement with experiment within ${\\}pm$4% with average deviation 2%, and are in agreement with theory within ${\\}pm$4.70% with average deviation 3.26%. The thermal conductivity values are in agreement with experiment within 11% with average deviation 8%, and are in agreement with theory within 4.2% with average deviation 2.8% over the temperature range considered. It is likely that the potential function can be used to predict both equilibrium and transport properties with reasonably good accuracies.\n
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\n \n\n \n \n Warren, E.\n\n\n \n \n \n \n \n The role of arithmetic structure in the transition from arithmetic to algebra.\n \n \n \n \n\n\n \n\n\n\n Mathematics Education Research Journal 2003 15:2, 15(2): 122–137. 2003.\n Publisher: Springer\n\n\n\n
\n\n\n\n \n \n \"ThePaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{warren2003,\n\ttitle = {The role of arithmetic structure in the transition from arithmetic to algebra},\n\tvolume = {15},\n\turl = {https://link.springer.com/article/10.1007/BF03217374},\n\tdoi = {10.1007/BF03217374},\n\tabstract = {This paper investigates students’ understanding of the associative law, commutative law, and addition and division as general processes after they have completed their primary school education. All these understandings are believed to assist successful transition from arithmetic to algebra. A written test was administered to 672 students. The results identified difficulties students are experiencing with these processes. Implications for teaching algebra at both primary and secondary levels are discussed.},\n\tnumber = {2},\n\tjournal = {Mathematics Education Research Journal 2003 15:2},\n\tauthor = {Warren, Elizabeth},\n\tyear = {2003},\n\tnote = {Publisher: Springer},\n\tpages = {122--137},\n}\n\n\n\n
\n
\n\n\n
\n This paper investigates students’ understanding of the associative law, commutative law, and addition and division as general processes after they have completed their primary school education. All these understandings are believed to assist successful transition from arithmetic to algebra. A written test was administered to 672 students. The results identified difficulties students are experiencing with these processes. Implications for teaching algebra at both primary and secondary levels are discussed.\n
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\n \n\n \n \n Plotkin, K. J.; and Maglieri, D. J.\n\n\n \n \n \n \n Sonic Boom Research: History and Future.\n \n \n \n\n\n \n\n\n\n In pages 1–11, Orlando, FL, 2003. \\AIAA Paper\\ 2003-3575\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{plotkin2003,\n\taddress = {Orlando, FL},\n\ttitle = {Sonic {Boom} {Research}: {History} and {Future}},\n\tisbn = {978-1-62410-095-6},\n\tdoi = {10.2514/6.2003-3575},\n\tabstract = {Sonic booms have been generated by aircraft ever since the X-1 exceeded Mach 1 in 1947. Within a few years sonic boom was understood by aerodynamicists to be the shock wave pattern from the aircraft - a rediscovery of a phenomenon already familiar to the ballistics community. Substantial flight test activity ensued to quantify booms. In parallel, a theoretical understanding of sonic booms grew rapidly. This paper reviews the progress of sonic boom measurements and theory over the past half century, showing the synergy between the two, the current state of the art, and problems that remain to be solved. © 2003 by Authors. Published by the American Institute of Aeronautics and Astronautics, Inc.},\n\tpublisher = {\\{AIAA Paper\\} 2003-3575},\n\tauthor = {Plotkin, Kenneth J. and Maglieri, Domenic J.},\n\tyear = {2003},\n\tpages = {1--11},\n}\n\n\n\n
\n
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\n Sonic booms have been generated by aircraft ever since the X-1 exceeded Mach 1 in 1947. Within a few years sonic boom was understood by aerodynamicists to be the shock wave pattern from the aircraft - a rediscovery of a phenomenon already familiar to the ballistics community. Substantial flight test activity ensued to quantify booms. In parallel, a theoretical understanding of sonic booms grew rapidly. This paper reviews the progress of sonic boom measurements and theory over the past half century, showing the synergy between the two, the current state of the art, and problems that remain to be solved. © 2003 by Authors. Published by the American Institute of Aeronautics and Astronautics, Inc.\n
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\n \n\n \n \n Goyne, C P; Stalker, R J; and Paull, A\n\n\n \n \n \n \n Skin-friction measurements in high-enthalpy hypersonic boundary layers.\n \n \n \n\n\n \n\n\n\n Journal of Fluid Mechanics, 485: 1–32. 2003.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{goyne2003,\n\ttitle = {Skin-friction measurements in high-enthalpy hypersonic boundary layers},\n\tvolume = {485},\n\tdoi = {10.1017/S0022112003003975},\n\tjournal = {Journal of Fluid Mechanics},\n\tauthor = {Goyne, C P and Stalker, R J and Paull, A},\n\tyear = {2003},\n\tpages = {1--32},\n}\n\n\n\n
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\n \n\n \n \n Mavriplis, D. J.\n\n\n \n \n \n \n \n Revisiting the least-squares procedure for gradient reconstruction on unstructured meshes.\n \n \n \n \n\n\n \n\n\n\n In 2003. AIAA Paper 2003-3986\n \n\n\n\n
\n\n\n\n \n \n \"RevisitingPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{mavriplis2003,\n\ttitle = {Revisiting the least-squares procedure for gradient reconstruction on unstructured meshes},\n\tisbn = {978-1-62410-086-4},\n\turl = {https://arc.aiaa.org/doi/10.2514/6.2003-3986},\n\tdoi = {10.2514/6.2003-3986},\n\tabstract = {The accuracy of the least-squares technique for gradient reconstruction on unstructured meshes is examined. While least-squares techniques produce accurate results on arbitrary isotropic unstructured meshes, serious difficulties exist for highly stretched meshes in the presence of surface curvature. In these situations, gradients are typically under-estimated by up to an order of magnitude. For vertex-based discretizations on triangular and quadrilateral meshes, and cell-centered discretizations on quadrilateral meshes, accuracy can be recovered using an inverse distance weighting in the least-squares construction. For cell-centered discretizations on triangles, both the unweighted and weighted least-squares constructions fail to provide suitable gradient estimates for highly stretched curved meshes. Good overall flow solution accuracy can be retained in spite of poor gradient estimates, due to the presence of flow alignment in exactly the same regions where the poor gradient accuracy is observed. However, the use of entropy fixes, or the discretization of physical viscous terms based on these gradients has the potential for generating large but subtle discretization errors, which vanish in regions with no appreciable surface curvature. © 2003 by Dimitri J. Mavriplis. Published by the American Institute of Aeronautics and Astronautics, Inc., with permission.},\n\tpublisher = {AIAA Paper 2003-3986},\n\tauthor = {Mavriplis, Dimitri J.},\n\tyear = {2003},\n}\n\n\n\n
\n
\n\n\n
\n The accuracy of the least-squares technique for gradient reconstruction on unstructured meshes is examined. While least-squares techniques produce accurate results on arbitrary isotropic unstructured meshes, serious difficulties exist for highly stretched meshes in the presence of surface curvature. In these situations, gradients are typically under-estimated by up to an order of magnitude. For vertex-based discretizations on triangular and quadrilateral meshes, and cell-centered discretizations on quadrilateral meshes, accuracy can be recovered using an inverse distance weighting in the least-squares construction. For cell-centered discretizations on triangles, both the unweighted and weighted least-squares constructions fail to provide suitable gradient estimates for highly stretched curved meshes. Good overall flow solution accuracy can be retained in spite of poor gradient estimates, due to the presence of flow alignment in exactly the same regions where the poor gradient accuracy is observed. However, the use of entropy fixes, or the discretization of physical viscous terms based on these gradients has the potential for generating large but subtle discretization errors, which vanish in regions with no appreciable surface curvature. © 2003 by Dimitri J. Mavriplis. Published by the American Institute of Aeronautics and Astronautics, Inc., with permission.\n
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\n \n\n \n \n Anderson, J. D\n\n\n \n \n \n \n Modern Compressible Flow: With Historical Perspective.\n \n \n \n\n\n \n\n\n\n McGraw-Hill, 3rd edition, 2003.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@book{anderson2003,\n\tedition = {3rd},\n\ttitle = {Modern {Compressible} {Flow}: {With} {Historical} {Perspective}},\n\tpublisher = {McGraw-Hill},\n\tauthor = {Anderson, John D},\n\tyear = {2003},\n}\n\n\n\n
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\n \n\n \n \n Ge, W.; and Li, J.\n\n\n \n \n \n \n Macro-scale phenomena reproduced in microscopic systems—pseudo-particle modeling of fluidization.\n \n \n \n\n\n \n\n\n\n Chemical Engineering Science, 58(8): 1565–1585. April 2003.\n Publisher: Pergamon\n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{ge2003,\n\ttitle = {Macro-scale phenomena reproduced in microscopic systems—pseudo-particle modeling of fluidization},\n\tvolume = {58},\n\tdoi = {10.1016/S0009-2509(02)00673-5},\n\tabstract = {Despite its wide applications, fluidization is not understood enough to satisfy our technical or academic interests. Cascading simulation approaches on different scales, with small-scale approaches provide constitutional correlations to larger scale approaches, is considered a practical way toward this direction. However, by physically reproducing many macro-scale phenomena in fluid flow and fluidization on micro-scales even below the traditional continuum limit, pseudo-particle modeling (PPM, Ge and Li (Proceedings of the Fifth International Conference on Circulating Fluidized Bed, Beijing, China, Science Press, Beijing, 1996) has suggested the possibility of a more straightforward and penetrating way. In this paper, traditional approaches are reviewed first and then PPM is discussed in full length and validated further. We demonstrate that it has maintained all necessities on the molecular level for comprehensive flow description, and the reproduced phenomena, such as bubbling, clustering and radial heterogeneity, have reflected the fundamental mechanism of their macro-scale counterparts despite the vast scale difference. With this digital miniature, every detail of the flow can be traced non-intrusively until the lowest level in classic physics and experiment with flexible parameters, which provides a unique tool for theoretical study and engineering predictions. Therefore, PPM is at least a useful complement, if not substitute, to traditional approaches. © 2003 Elsevier Science Ltd. All rights reserved.},\n\tnumber = {8},\n\tjournal = {Chemical Engineering Science},\n\tauthor = {Ge, Wei and Li, Jinghai},\n\tmonth = apr,\n\tyear = {2003},\n\tnote = {Publisher: Pergamon},\n\tkeywords = {Dynamic simulation, Fluidization, Multi-scale, Particle method, Scale-up, Transport process},\n\tpages = {1565--1585},\n}\n\n\n\n
\n
\n\n\n
\n Despite its wide applications, fluidization is not understood enough to satisfy our technical or academic interests. Cascading simulation approaches on different scales, with small-scale approaches provide constitutional correlations to larger scale approaches, is considered a practical way toward this direction. However, by physically reproducing many macro-scale phenomena in fluid flow and fluidization on micro-scales even below the traditional continuum limit, pseudo-particle modeling (PPM, Ge and Li (Proceedings of the Fifth International Conference on Circulating Fluidized Bed, Beijing, China, Science Press, Beijing, 1996) has suggested the possibility of a more straightforward and penetrating way. In this paper, traditional approaches are reviewed first and then PPM is discussed in full length and validated further. We demonstrate that it has maintained all necessities on the molecular level for comprehensive flow description, and the reproduced phenomena, such as bubbling, clustering and radial heterogeneity, have reflected the fundamental mechanism of their macro-scale counterparts despite the vast scale difference. With this digital miniature, every detail of the flow can be traced non-intrusively until the lowest level in classic physics and experiment with flexible parameters, which provides a unique tool for theoretical study and engineering predictions. Therefore, PPM is at least a useful complement, if not substitute, to traditional approaches. © 2003 Elsevier Science Ltd. All rights reserved.\n
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\n \n\n \n \n Karl, S.; Schramm, J. M.; and Hannemann, K.\n\n\n \n \n \n \n High Enthalpy Cylinder Flow in HEG: A Basis for CFD Validation.\n \n \n \n\n\n \n\n\n\n In Orlando, FL, June 2003. AIAA 2003-4252\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{karl2003,\n\taddress = {Orlando, FL},\n\ttitle = {High {Enthalpy} {Cylinder} {Flow} in {HEG}: {A} {Basis} for {CFD} {Validation}},\n\tpublisher = {AIAA 2003-4252},\n\tauthor = {Karl, Sebastian and Schramm, Jan Martinez and Hannemann, Klaus},\n\tmonth = jun,\n\tyear = {2003},\n}\n\n\n\n
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\n \n\n \n \n Nompelis, I.; Candler, G. V; Holden, M S; and Wadhams, T P\n\n\n \n \n \n \n Computational Investigation of Hypersonic Viscous/Inviscid Interactions in High Enthalpy Flows.\n \n \n \n\n\n \n\n\n\n In 2003. \\AIAA Paper\\ 2003-3642\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{nompelis2003,\n\ttitle = {Computational {Investigation} of {Hypersonic} {Viscous}/{Inviscid} {Interactions} in {High} {Enthalpy} {Flows}},\n\tpublisher = {\\{AIAA Paper\\} 2003-3642},\n\tauthor = {Nompelis, Ioannis and Candler, Graham V and Holden, M S and Wadhams, T P},\n\tyear = {2003},\n}\n\n\n\n
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\n \n\n \n \n Palmer, G. E; and Wright, M. J\n\n\n \n \n \n \n Comparison of Methods to Compute High-Temperature Gas Viscosity.\n \n \n \n\n\n \n\n\n\n Journal of Thermophysics and Heat Transfer, 17(2): 232–239. 2003.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{palmer2003,\n\ttitle = {Comparison of {Methods} to {Compute} {High}-{Temperature} {Gas} {Viscosity}},\n\tvolume = {17},\n\tdoi = {10.2514/2.6756},\n\tnumber = {2},\n\tjournal = {Journal of Thermophysics and Heat Transfer},\n\tauthor = {Palmer, Grant E and Wright, Michael J},\n\tyear = {2003},\n\tpages = {232--239},\n}\n\n\n\n
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\n  \n 2002\n \n \n (9)\n \n \n
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\n \n\n \n \n Smith, J.\n\n\n \n \n \n \n Evolved Composite Structures for Atlas V.\n \n \n \n\n\n \n\n\n\n In Indianapolis, Indiana, July 2002. AIAA\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{smith2002,\n\taddress = {Indianapolis, Indiana},\n\ttitle = {Evolved {Composite} {Structures} for {Atlas} {V}},\n\tdoi = {10.2514/6.2002-4201},\n\tpublisher = {AIAA},\n\tauthor = {Smith, John},\n\tmonth = jul,\n\tyear = {2002},\n}\n\n\n\n
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\n \n\n \n \n Sowers, G.\n\n\n \n \n \n \n First Flight - Atlas V Evolved Expendable Launch Vehicle.\n \n \n \n\n\n \n\n\n\n In Indianapolis, Indiana, July 2002. AIAA\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{sowers2002,\n\taddress = {Indianapolis, Indiana},\n\ttitle = {First {Flight} - {Atlas} {V} {Evolved} {Expendable} {Launch} {Vehicle}},\n\tdoi = {10.2514/6.2002-4204},\n\tpublisher = {AIAA},\n\tauthor = {Sowers, George},\n\tmonth = jul,\n\tyear = {2002},\n}\n\n\n\n
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\n \n\n \n \n Doihara, R.; and Nishida, M.\n\n\n \n \n \n \n Thermochemical nonequilibrium viscous shock layer studies of the orbital reentry experiment (OREX) vehicle.\n \n \n \n\n\n \n\n\n\n Shock Waves, 11(5): 331–339. April 2002.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{doihara2002,\n\ttitle = {Thermochemical nonequilibrium viscous shock layer studies of the orbital reentry experiment ({OREX}) vehicle},\n\tvolume = {11},\n\tissn = {1432-2153},\n\tdoi = {10.1007/s001930200119},\n\tabstract = {In 1994, the Orbital Reentry Experiment (OREX) was conducted by the National Aerospace Laboratory and National Space Development Agency of Japan. During this experiment aerodynamic heating and saturated ion current were successfully measured. In this paper, the thermochemical nonequilibrium shock layer of the OREX vehicle has been reconstructed using a VSL (Viscous Shock Layer) numerical simulation. In addition, heating to the OREX vehicle and electron density have been calculated and compared with the flight data. The numerical simulation has been made for the flight conditions at altitudes ranging from 96.7 km to 59.6 km, using a three temperature model composed of translational-rotational, vibrational and electron-electronic temperatures. The catalytic efficiency of the coating material on the nose of the vehicle was determined by comparing the flight data for heat flux with the numerical result for the finite catalytic wall. The calculated electron density values were in approximate agreement with the flight values.},\n\tlanguage = {en},\n\tnumber = {5},\n\turldate = {2023-06-22},\n\tjournal = {Shock Waves},\n\tauthor = {Doihara, R. and Nishida, M.},\n\tmonth = apr,\n\tyear = {2002},\n\tkeywords = {Key words: Thermochemical nonequilibrium, Atmospheric entry, Strong shock wave, Aerodynamic heating, Viscous shock layer, High temperature gas},\n\tpages = {331--339},\n}\n\n\n\n\n\n\n\n
\n
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\n In 1994, the Orbital Reentry Experiment (OREX) was conducted by the National Aerospace Laboratory and National Space Development Agency of Japan. During this experiment aerodynamic heating and saturated ion current were successfully measured. In this paper, the thermochemical nonequilibrium shock layer of the OREX vehicle has been reconstructed using a VSL (Viscous Shock Layer) numerical simulation. In addition, heating to the OREX vehicle and electron density have been calculated and compared with the flight data. The numerical simulation has been made for the flight conditions at altitudes ranging from 96.7 km to 59.6 km, using a three temperature model composed of translational-rotational, vibrational and electron-electronic temperatures. The catalytic efficiency of the coating material on the nose of the vehicle was determined by comparing the flight data for heat flux with the numerical result for the finite catalytic wall. The calculated electron density values were in approximate agreement with the flight values.\n
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\n \n\n \n \n McBride, B. J; Zehe, M. J; and Gordon, S.\n\n\n \n \n \n \n NASA Glenn Coefficients for Calculating Thermodynamic Properties of Individual Species.\n \n \n \n\n\n \n\n\n\n Technical Report Cleveland, Ohio, 2002.\n Issue: NASA/TP-2002-211556\n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@techreport{mcbride2002,\n\taddress = {Cleveland, Ohio},\n\ttitle = {{NASA} {Glenn} {Coefficients} for {Calculating} {Thermodynamic} {Properties} of {Individual} {Species}},\n\tauthor = {McBride, Bonnie J and Zehe, Michael J and Gordon, Sanford},\n\tyear = {2002},\n\tnote = {Issue: NASA/TP-2002-211556},\n}\n\n\n\n
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\n \n\n \n \n Vincenti, W. G; and Kruger, C. H.\n\n\n \n \n \n \n Introduction to Physical Gas Dynamics.\n \n \n \n\n\n \n\n\n\n Krieger Publishing Company, 2002.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@book{vincenti2002,\n\ttitle = {Introduction to {Physical} {Gas} {Dynamics}},\n\tpublisher = {Krieger Publishing Company},\n\tauthor = {Vincenti, Walter G and Charles H. Kruger, Jr.},\n\tyear = {2002},\n}\n\n\n\n
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\n \n\n \n \n Plotkin, K. J.; and Page, J. A.\n\n\n \n \n \n \n Extrapolation of Sonic Boom Signatures from CFD solutions.\n \n \n \n\n\n \n\n\n\n In pages 1–6, Reno, NV, 2002. \\AIAA Paper\\ 2002-0922\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{plotkin2002,\n\taddress = {Reno, NV},\n\ttitle = {Extrapolation of {Sonic} {Boom} {Signatures} from {CFD} solutions},\n\tdoi = {10.2514/6.2002-922},\n\tabstract = {Traditional sonic boom modeling is based on area rule aerodynamic analysis near the vehicle, followed by quasi-acoustic propagation to the ground. Modern aerodynamic design uses Computational Fluid Dynamics (CFD). When designing reduced sonic boom aircraft configurations, there are subtle details which demand that level of analysis. The local detail implicit in CFD solutions is, however, not compatible with the assumptions implicit in customary sonic boom propagation methods. This paper reviews various approaches to coupling CFD solutions to methods for propagation of sonic boom to the ground. © 2002 by Kenneth J. Plotkin and Juliet A. Page.},\n\tpublisher = {\\{AIAA Paper\\} 2002-0922},\n\tauthor = {Plotkin, Kenneth J. and Page, Juliet A.},\n\tyear = {2002},\n\tpages = {1--6},\n}\n\n\n\n
\n
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\n Traditional sonic boom modeling is based on area rule aerodynamic analysis near the vehicle, followed by quasi-acoustic propagation to the ground. Modern aerodynamic design uses Computational Fluid Dynamics (CFD). When designing reduced sonic boom aircraft configurations, there are subtle details which demand that level of analysis. The local detail implicit in CFD solutions is, however, not compatible with the assumptions implicit in customary sonic boom propagation methods. This paper reviews various approaches to coupling CFD solutions to methods for propagation of sonic boom to the ground. © 2002 by Kenneth J. Plotkin and Juliet A. Page.\n
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\n \n\n \n \n Qin, X.; Xiao, X.; Puri, I. K; and Aggarwal, S. K\n\n\n \n \n \n \n Effect of varying composition on temperature reconstructions obtained from refractive index measurements in flames.\n \n \n \n\n\n \n\n\n\n Combustion and Flame, 128(1): 121–132. 2002.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{qin2002,\n\ttitle = {Effect of varying composition on temperature reconstructions obtained from refractive index measurements in flames},\n\tvolume = {128},\n\tnumber = {1},\n\tjournal = {Combustion and Flame},\n\tauthor = {Qin, Xiao and Xiao, Xudong and Puri, Ishwar K and Aggarwal, Suresh K},\n\tyear = {2002},\n\tpages = {121--132},\n}\n\n\n\n
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\n \n\n \n \n Shkarayev, S.; Raman, A.; and Tessler, A.\n\n\n \n \n \n \n Computational and Experimental Validation Enabling a Viable In-Flight Structural Health Monitoring Technology.\n \n \n \n\n\n \n\n\n\n In 2002. \n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{shkarayev2002,\n\ttitle = {Computational and {Experimental} {Validation} {Enabling} a {Viable} {In}-{Flight} {Structural} {Health} {Monitoring} {Technology}},\n\tauthor = {Shkarayev, S. and Raman, A. and Tessler, A.},\n\tyear = {2002},\n}\n\n\n\n
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\n \n\n \n \n Laumanns, M.; and Ocenasek, J.\n\n\n \n \n \n \n Bayesian Optimization Algorithms for Multi-objective Optimization.\n \n \n \n\n\n \n\n\n\n In Guervós, J. J. M.; Adamidis, P.; Beyer, H.; Schwefel, H.; and Fernández-Villacañas, J., editor(s), pages 298–307, Berlin, Heidelberg, 2002. Springer Berlin Heidelberg\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{laumanns2002,\n\taddress = {Berlin, Heidelberg},\n\ttitle = {Bayesian {Optimization} {Algorithms} for {Multi}-objective {Optimization}},\n\tisbn = {978-3-540-45712-1},\n\tabstract = {In recent years, several researchers have concentrated on using probabilistic models in evolutionary algorithms. These Estimation Distribution Algorithms (EDA) incorporate methods for automated learning of correlations between variables of the encoded solutions. The process of sampling new individuals from a probabilistic model respects these mutual dependencies such that disruption of important building blocks is avoided, in comparison with classical recombination operators. The goal of this paper is to investigate the usefulness of this concept in multi-objective optimization, where the aim is to approximate the set of Pareto-optimal solutions. We integrate the model building and sampling techniques of a special EDA called Bayesian Optimization Algorithm, based on binary decision trees, into an evolutionary multi-objective optimizer using a special selection scheme. The behavior of the resulting Bayesian Multi-objective Optimization Algorithm (BMOA) is empirically investigated on the multi-objective knapsack problem.},\n\tpublisher = {Springer Berlin Heidelberg},\n\tauthor = {Laumanns, Marco and Ocenasek, Jiri},\n\teditor = {Guervós, Juan Julián Merelo and Adamidis, Panagiotis and Beyer, Hans-Georg and Schwefel, Hans-Paul and Fernández-Villacañas, José-Luis},\n\tyear = {2002},\n\tpages = {298--307},\n}\n\n\n\n
\n
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\n In recent years, several researchers have concentrated on using probabilistic models in evolutionary algorithms. These Estimation Distribution Algorithms (EDA) incorporate methods for automated learning of correlations between variables of the encoded solutions. The process of sampling new individuals from a probabilistic model respects these mutual dependencies such that disruption of important building blocks is avoided, in comparison with classical recombination operators. The goal of this paper is to investigate the usefulness of this concept in multi-objective optimization, where the aim is to approximate the set of Pareto-optimal solutions. We integrate the model building and sampling techniques of a special EDA called Bayesian Optimization Algorithm, based on binary decision trees, into an evolutionary multi-objective optimizer using a special selection scheme. The behavior of the resulting Bayesian Multi-objective Optimization Algorithm (BMOA) is empirically investigated on the multi-objective knapsack problem.\n
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\n  \n 2001\n \n \n (10)\n \n \n
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\n \n\n \n \n Kuntz, D W; Hassan, B; and Potter, D L\n\n\n \n \n \n \n Predictions of Ablating Hypersonic Vehicles Using an Iterative Coupled Fluid/Thermal Approach.\n \n \n \n\n\n \n\n\n\n Journal of Thermophysics and Heat Transfer, 15(2): 129–139. 2001.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{kuntz2001,\n\ttitle = {Predictions of {Ablating} {Hypersonic} {Vehicles} {Using} an {Iterative} {Coupled} {Fluid}/{Thermal} {Approach}},\n\tvolume = {15},\n\tdoi = {10.2514/2.6594},\n\tnumber = {2},\n\tjournal = {Journal of Thermophysics and Heat Transfer},\n\tauthor = {Kuntz, D W and Hassan, B and Potter, D L},\n\tyear = {2001},\n\tpages = {129--139},\n}\n\n\n\n
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\n \n\n \n \n Park, C.; Jaffe, R. L.; and Partridge, H.\n\n\n \n \n \n \n Chemical-Kinetic Parameters of Hyperbolic Earth Entry.\n \n \n \n\n\n \n\n\n\n Journal of Thermophysics and Heat Transfer, 15(1): 76–90. January 2001.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{park2001,\n\ttitle = {Chemical-{Kinetic} {Parameters} of {Hyperbolic} {Earth} {Entry}},\n\tvolume = {15},\n\tissn = {0887-8722, 1533-6808},\n\tdoi = {10.2514/2.6582},\n\tlanguage = {en},\n\tnumber = {1},\n\turldate = {2023-06-22},\n\tjournal = {Journal of Thermophysics and Heat Transfer},\n\tauthor = {Park, Chul and Jaffe, Richard L. and Partridge, Harry},\n\tmonth = jan,\n\tyear = {2001},\n\tpages = {76--90},\n}\n\n\n\n\n\n\n\n
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\n \n\n \n \n Bowcutt, K. G\n\n\n \n \n \n \n \n Multidisciplinary Optimization of Airbreathing Hypersonic Vehicles.\n \n \n \n \n\n\n \n\n\n\n Journal of Propulsion and Power, 17(6). 2001.\n \n\n\n\n
\n\n\n\n \n \n \"MultidisciplinaryPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{bowcutt2001,\n\ttitle = {Multidisciplinary {Optimization} of {Airbreathing} {Hypersonic} {Vehicles}},\n\tvolume = {17},\n\turl = {http://arc.aiaa.org},\n\tdoi = {10.2514/2.5893},\n\tabstract = {Airbreathing hypersonic aircraft and missiles are characterized by a high degree of interdependence between airframe and engine. For nonaxisymmetric vehicles the propulsion system exerts a major inn uence on vehicle lift and pitching moment; this in turn inn uences vehicle stability, control, and overall mission performance. Because of strong interactions between the airframe and engine, conceptual design of this class of vehicle requires a multidisciplinary design optimization (MDO) process that can simultaneously account for the impact of selected geometric variables on all vehicle subsystems. This paper describes the development and implementation of an MDO design system that combines propulsion and external aerodynamic forces, mass properties and internal volumetric modeling, and performs geometric optimization of a hypersonic cruise missile to maximize overall mission range. The result is a conn guration with range 46\\% greater than the initial baseline. Such a dramatic performance increase is indicative not only of the power of optimization, but of the diff culty in conn guring hypersonic vehicles to synergize the interaction of all vehicle components without MDO methods. Nomenclature D = drag g = gravitational acceleration I sp = specii c impulse I yy = pitch moment of inertia K = centrifugal relief factor L = lift L p = propulsive lift`chine lift`lift`chine = chine length`cowl length`length`cowl = nozzle cowl length M ® = pitching-moment derivative P q = pitch acceleration R = range r E = Earth's radius T = thrust in ight direction Q T = thrust magnitude T 2 = time to double V = velocity W = weight W 0 = weight modii ed by centrifugal relief Q W = required cruise aerodynamic lift w f = fuel ow rate x eng = engine axial location ® = angle of attack µ cant = engine cant angle µ nose = upper-body nose angle µ T = thrust vector angle},\n\tnumber = {6},\n\turldate = {2021-05-28},\n\tjournal = {Journal of Propulsion and Power},\n\tauthor = {Bowcutt, Kevin G},\n\tyear = {2001},\n}\n\n\n\n
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\n Airbreathing hypersonic aircraft and missiles are characterized by a high degree of interdependence between airframe and engine. For nonaxisymmetric vehicles the propulsion system exerts a major inn uence on vehicle lift and pitching moment; this in turn inn uences vehicle stability, control, and overall mission performance. Because of strong interactions between the airframe and engine, conceptual design of this class of vehicle requires a multidisciplinary design optimization (MDO) process that can simultaneously account for the impact of selected geometric variables on all vehicle subsystems. This paper describes the development and implementation of an MDO design system that combines propulsion and external aerodynamic forces, mass properties and internal volumetric modeling, and performs geometric optimization of a hypersonic cruise missile to maximize overall mission range. The result is a conn guration with range 46% greater than the initial baseline. Such a dramatic performance increase is indicative not only of the power of optimization, but of the diff culty in conn guring hypersonic vehicles to synergize the interaction of all vehicle components without MDO methods. Nomenclature D = drag g = gravitational acceleration I sp = specii c impulse I yy = pitch moment of inertia K = centrifugal relief factor L = lift L p = propulsive lift`chine lift`lift`chine = chine length`cowl length`length`cowl = nozzle cowl length M ® = pitching-moment derivative P q = pitch acceleration R = range r E = Earth's radius T = thrust in ight direction Q T = thrust magnitude T 2 = time to double V = velocity W = weight W 0 = weight modii ed by centrifugal relief Q W = required cruise aerodynamic lift w f = fuel ow rate x eng = engine axial location ® = angle of attack µ cant = engine cant angle µ nose = upper-body nose angle µ T = thrust vector angle\n
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\n \n\n \n \n Bowcutt, K. G\n\n\n \n \n \n \n \n Multidisciplinary Optimization of Airbreathing Hypersonic Vehicles.\n \n \n \n \n\n\n \n\n\n\n Journal of Propulsion and Power, 17(6). 2001.\n \n\n\n\n
\n\n\n\n \n \n \"MultidisciplinaryPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{bowcutt2001b,\n\ttitle = {Multidisciplinary {Optimization} of {Airbreathing} {Hypersonic} {Vehicles}},\n\tvolume = {17},\n\turl = {http://arc.aiaa.org},\n\tdoi = {10.2514/2.5893},\n\tabstract = {Airbreathing hypersonic aircraft and missiles are characterized by a high degree of interdependence between airframe and engine. For nonaxisymmetric vehicles the propulsion system exerts a major inn uence on vehicle lift and pitching moment; this in turn inn uences vehicle stability, control, and overall mission performance. Because of strong interactions between the airframe and engine, conceptual design of this class of vehicle requires a multidisciplinary design optimization (MDO) process that can simultaneously account for the impact of selected geometric variables on all vehicle subsystems. This paper describes the development and implementation of an MDO design system that combines propulsion and external aerodynamic forces, mass properties and internal volumetric modeling, and performs geometric optimization of a hypersonic cruise missile to maximize overall mission range. The result is a conn guration with range 46\\% greater than the initial baseline. Such a dramatic performance increase is indicative not only of the power of optimization, but of the diff culty in conn guring hypersonic vehicles to synergize the interaction of all vehicle components without MDO methods. Nomenclature D = drag g = gravitational acceleration I sp = specii c impulse I yy = pitch moment of inertia K = centrifugal relief factor L = lift L p = propulsive lift`chine lift`lift`chine = chine length`cowl length`length`cowl = nozzle cowl length M ® = pitching-moment derivative P q = pitch acceleration R = range r E = Earth's radius T = thrust in ight direction Q T = thrust magnitude T 2 = time to double V = velocity W = weight W 0 = weight modii ed by centrifugal relief Q W = required cruise aerodynamic lift w f = fuel ow rate x eng = engine axial location ® = angle of attack µ cant = engine cant angle µ nose = upper-body nose angle µ T = thrust vector angle},\n\tnumber = {6},\n\tjournal = {Journal of Propulsion and Power},\n\tauthor = {Bowcutt, Kevin G},\n\tyear = {2001},\n}\n\n\n\n
\n
\n\n\n
\n Airbreathing hypersonic aircraft and missiles are characterized by a high degree of interdependence between airframe and engine. For nonaxisymmetric vehicles the propulsion system exerts a major inn uence on vehicle lift and pitching moment; this in turn inn uences vehicle stability, control, and overall mission performance. Because of strong interactions between the airframe and engine, conceptual design of this class of vehicle requires a multidisciplinary design optimization (MDO) process that can simultaneously account for the impact of selected geometric variables on all vehicle subsystems. This paper describes the development and implementation of an MDO design system that combines propulsion and external aerodynamic forces, mass properties and internal volumetric modeling, and performs geometric optimization of a hypersonic cruise missile to maximize overall mission range. The result is a conn guration with range 46% greater than the initial baseline. Such a dramatic performance increase is indicative not only of the power of optimization, but of the diff culty in conn guring hypersonic vehicles to synergize the interaction of all vehicle components without MDO methods. Nomenclature D = drag g = gravitational acceleration I sp = specii c impulse I yy = pitch moment of inertia K = centrifugal relief factor L = lift L p = propulsive lift`chine lift`lift`chine = chine length`cowl length`length`cowl = nozzle cowl length M ® = pitching-moment derivative P q = pitch acceleration R = range r E = Earth's radius T = thrust in ight direction Q T = thrust magnitude T 2 = time to double V = velocity W = weight W 0 = weight modii ed by centrifugal relief Q W = required cruise aerodynamic lift w f = fuel ow rate x eng = engine axial location ® = angle of attack µ cant = engine cant angle µ nose = upper-body nose angle µ T = thrust vector angle\n
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\n \n\n \n \n Bowcutt, K. G\n\n\n \n \n \n \n Multidisciplinary Optimization of Airbreathing Hypersonic Vehicles.\n \n \n \n\n\n \n\n\n\n Journal of Propulsion and Power, 17(6). 2001.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{bowcutt2001a,\n\ttitle = {Multidisciplinary {Optimization} of {Airbreathing} {Hypersonic} {Vehicles}},\n\tvolume = {17},\n\tdoi = {10.2514/2.5893},\n\tabstract = {Airbreathing hypersonic aircraft and missiles are characterized by a high degree of interdependence between airframe and engine. For nonaxisymmetric vehicles the propulsion system exerts a major inn uence on vehicle lift and pitching moment; this in turn inn uences vehicle stability, control, and overall mission performance. Because of strong interactions between the airframe and engine, conceptual design of this class of vehicle requires a multidisciplinary design optimization (MDO) process that can simultaneously account for the impact of selected geometric variables on all vehicle subsystems. This paper describes the development and implementation of an MDO design system that combines propulsion and external aerodynamic forces, mass properties and internal volumetric modeling, and performs geometric optimization of a hypersonic cruise missile to maximize overall mission range. The result is a conn guration with range 46\\% greater than the initial baseline. Such a dramatic performance increase is indicative not only of the power of optimization, but of the diff culty in conn guring hypersonic vehicles to synergize the interaction of all vehicle components without MDO methods. Nomenclature D = drag g = gravitational acceleration I sp = specii c impulse I yy = pitch moment of inertia K = centrifugal relief factor L = lift L p = propulsive lift`chine lift`lift`chine = chine length`cowl length`length`cowl = nozzle cowl length M ® = pitching-moment derivative P q = pitch acceleration R = range r E = Earth's radius T = thrust in ight direction Q T = thrust magnitude T 2 = time to double V = velocity W = weight W 0 = weight modii ed by centrifugal relief Q W = required cruise aerodynamic lift w f = fuel ow rate x eng = engine axial location ® = angle of attack µ cant = engine cant angle µ nose = upper-body nose angle µ T = thrust vector angle},\n\tnumber = {6},\n\tjournal = {Journal of Propulsion and Power},\n\tauthor = {Bowcutt, Kevin G},\n\tyear = {2001},\n}\n\n\n\n
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\n Airbreathing hypersonic aircraft and missiles are characterized by a high degree of interdependence between airframe and engine. For nonaxisymmetric vehicles the propulsion system exerts a major inn uence on vehicle lift and pitching moment; this in turn inn uences vehicle stability, control, and overall mission performance. Because of strong interactions between the airframe and engine, conceptual design of this class of vehicle requires a multidisciplinary design optimization (MDO) process that can simultaneously account for the impact of selected geometric variables on all vehicle subsystems. This paper describes the development and implementation of an MDO design system that combines propulsion and external aerodynamic forces, mass properties and internal volumetric modeling, and performs geometric optimization of a hypersonic cruise missile to maximize overall mission range. The result is a conn guration with range 46% greater than the initial baseline. Such a dramatic performance increase is indicative not only of the power of optimization, but of the diff culty in conn guring hypersonic vehicles to synergize the interaction of all vehicle components without MDO methods. Nomenclature D = drag g = gravitational acceleration I sp = specii c impulse I yy = pitch moment of inertia K = centrifugal relief factor L = lift L p = propulsive lift`chine lift`lift`chine = chine length`cowl length`length`cowl = nozzle cowl length M ® = pitching-moment derivative P q = pitch acceleration R = range r E = Earth's radius T = thrust in ight direction Q T = thrust magnitude T 2 = time to double V = velocity W = weight W 0 = weight modii ed by centrifugal relief Q W = required cruise aerodynamic lift w f = fuel ow rate x eng = engine axial location ® = angle of attack µ cant = engine cant angle µ nose = upper-body nose angle µ T = thrust vector angle\n
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\n \n\n \n \n Dowell, E. H; and Hall, K. C\n\n\n \n \n \n \n \n Modeling of Fluid-Structure Interaction.\n \n \n \n \n\n\n \n\n\n\n Annual Review of Fluid Mechanics, 33: 445–490. November 2001.\n Publisher: Annual Reviews 4139 El Camino Way, P.O. Box 10139, Palo Alto, CA 94303-0139, USA\n\n\n\n
\n\n\n\n \n \n \"ModelingPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n\n\n\n
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@article{dowell2001,\n\ttitle = {Modeling of {Fluid}-{Structure} {Interaction}},\n\tvolume = {33},\n\turl = {https://www.annualreviews.org/doi/abs/10.1146/annurev.fluid.33.1.445},\n\tdoi = {10.1146/ANNUREV.FLUID.33.1.445},\n\tabstract = {▪ Abstract The interaction of a flexible structure with a flowing fluid in which it is submersed or by which it is surrounded gives rise to a rich variety of physical phenomena with applications in...},\n\tjournal = {Annual Review of Fluid Mechanics},\n\tauthor = {Dowell, Earl H and Hall, Kenneth C},\n\tmonth = nov,\n\tyear = {2001},\n\tnote = {Publisher: Annual Reviews  4139 El Camino Way, P.O. Box 10139, Palo Alto, CA 94303-0139, USA},\n\tkeywords = {aeroelasticity, nonlinear dynamics, reduced-order models, time linearization},\n\tpages = {445--490},\n}\n\n\n\n
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\n ▪ Abstract The interaction of a flexible structure with a flowing fluid in which it is submersed or by which it is surrounded gives rise to a rich variety of physical phenomena with applications in...\n
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\n \n\n \n \n Katz, J.; and Plotkin, A.\n\n\n \n \n \n \n Low-Speed Aerodynamics.\n \n \n \n\n\n \n\n\n\n Cambridge University Press, 2nd edition, 2001.\n \n\n\n\n
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@book{katz2001,\n\tedition = {2nd},\n\ttitle = {Low-{Speed} {Aerodynamics}},\n\tpublisher = {Cambridge University Press},\n\tauthor = {Katz, Joseph and Plotkin, Allen},\n\tyear = {2001},\n}\n\n\n\n
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\n \n\n \n \n Harvey, J K; Holden, M S; and Wadhams, T P\n\n\n \n \n \n \n Code Validation Study of Laminar Shock/Boundary Layer and Shock/Shock Interactions in Hypersonic Flow, Part B: Comparison with Navier-Stokes and DSMC Solutions.\n \n \n \n\n\n \n\n\n\n In 2001. \\AIAA Paper\\ 2001-1031\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{harvey2001a,\n\ttitle = {Code {Validation} {Study} of {Laminar} {Shock}/{Boundary} {Layer} and {Shock}/{Shock} {Interactions} in {Hypersonic} {Flow}, {Part} {B}: {Comparison} with {Navier}-{Stokes} and {DSMC} {Solutions}},\n\tpublisher = {\\{AIAA Paper\\} 2001-1031},\n\tauthor = {Harvey, J K and Holden, M S and Wadhams, T P},\n\tyear = {2001},\n}\n\n\n\n
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\n \n\n \n \n Harvey, J K; Holden, M S; and Wadhams, T P\n\n\n \n \n \n \n Code Validation Study of Laminar Shock/Boundary Layer and Shock/Shock Interactions in Hypersonic Flow, Part A: Experimental Measurements.\n \n \n \n\n\n \n\n\n\n In 2001. \\AIAA Paper\\ 2001-1031\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{harvey2001,\n\ttitle = {Code {Validation} {Study} of {Laminar} {Shock}/{Boundary} {Layer} and {Shock}/{Shock} {Interactions} in {Hypersonic} {Flow}, {Part} {A}: {Experimental} {Measurements}},\n\tpublisher = {\\{AIAA Paper\\} 2001-1031},\n\tauthor = {Harvey, J K and Holden, M S and Wadhams, T P},\n\tyear = {2001},\n}\n\n\n\n
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\n \n\n \n \n Shkarayev, S.; Krashanitsa, R.; and Tessler, A.\n\n\n \n \n \n \n An Inverse Interpolation Method Utilizing In-Flight Strain Measurements for Determining Loads and Structural Response of Aerospace Vehicles.\n \n \n \n\n\n \n\n\n\n In 2001. \n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{shkarayev2001,\n\ttitle = {An {Inverse} {Interpolation} {Method} {Utilizing} {In}-{Flight} {Strain} {Measurements} for {Determining} {Loads} and {Structural} {Response} of {Aerospace} {Vehicles}},\n\tauthor = {Shkarayev, S. and Krashanitsa, R. and Tessler, A.},\n\tyear = {2001},\n}\n\n\n\n
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\n  \n 2000\n \n \n (9)\n \n \n
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\n \n\n \n \n Buldakov, M A; Matrosov, I I; and Cherepanov, V N\n\n\n \n \n \n \n Temperature Dependence of Polarizability of Diatomic Homonuclear Molecules.\n \n \n \n\n\n \n\n\n\n Molecular Spectroscopy, 89(1): 44–48. 2000.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{buldakov2000,\n\ttitle = {Temperature {Dependence} of {Polarizability} of {Diatomic} {Homonuclear} {Molecules}},\n\tvolume = {89},\n\tdoi = {10.1134/BF03355985},\n\tnumber = {1},\n\tjournal = {Molecular Spectroscopy},\n\tauthor = {Buldakov, M A and Matrosov, I I and Cherepanov, V N},\n\tyear = {2000},\n\tpages = {44--48},\n}\n\n\n\n
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\n \n\n \n \n Selle, S.; and Riedel, U.\n\n\n \n \n \n \n Transport Coefficients of Reacting Air at High Temperatures.\n \n \n \n\n\n \n\n\n\n In Reno, NV, January 2000. \\AIAA Paper\\ 2000-0211\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{selle2000,\n\taddress = {Reno, NV},\n\ttitle = {Transport {Coefficients} of {Reacting} {Air} at {High} {Temperatures}},\n\tdoi = {10.2514/6.2000-211},\n\tpublisher = {\\{AIAA Paper\\} 2000-0211},\n\tauthor = {Selle, Stefan and Riedel, Uwe},\n\tmonth = jan,\n\tyear = {2000},\n}\n\n\n\n
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\n \n\n \n \n Anderson, L. W.; Jacobs, J.; Schramm, S.; and Splittgerber, F.\n\n\n \n \n \n \n School transitions: beginning of the end or a new beginning?.\n \n \n \n\n\n \n\n\n\n International Journal of Educational Research, 33(4): 325–339. 2000.\n Publisher: Pergamon\n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@article{anderson2000,\n\ttitle = {School transitions: beginning of the end or a new beginning?},\n\tvolume = {33},\n\tdoi = {10.1016/S0883-0355(00)00020-3},\n\tabstract = {Moving from elementary to middle/junior high school or from middle/junior high to high school is difficult for most students and especially problematic for some. This chapter explores the reasons that these transitions are difficult, the kinds of students that have the greatest difficulty with transitions, and the process of disengagement from school that too often follows unsuccessful transitions. Facilitating successful transitions requires that attention be paid to students' preparedness for the transition and the kinds of support students need before, during, and after the transition. The chapter concludes with a series of recommendations for facilitating successful transitions. © 2000 Published by Elsevier Science Ltd.},\n\tnumber = {4},\n\tjournal = {International Journal of Educational Research},\n\tauthor = {Anderson, Lorin W. and Jacobs, Jacque and Schramm, Susan and Splittgerber, Fred},\n\tyear = {2000},\n\tnote = {Publisher: Pergamon},\n\tpages = {325--339},\n}\n\n\n\n
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\n Moving from elementary to middle/junior high school or from middle/junior high to high school is difficult for most students and especially problematic for some. This chapter explores the reasons that these transitions are difficult, the kinds of students that have the greatest difficulty with transitions, and the process of disengagement from school that too often follows unsuccessful transitions. Facilitating successful transitions requires that attention be paid to students' preparedness for the transition and the kinds of support students need before, during, and after the transition. The chapter concludes with a series of recommendations for facilitating successful transitions. © 2000 Published by Elsevier Science Ltd.\n
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\n \n\n \n \n Yanta, W. J.; Spring, W. C.; Neal, D. R.; Hamrick, D. R.; Copland, R. J.; Lafferty, J. F.; Collier, A. S.; Bell, R. L.; Pezzaniti, L.; Banish, M.; and Shaw, R.\n\n\n \n \n \n \n Near- and farfield measurements of aero-optical effects due to propagation through hypersonic flows.\n \n \n \n\n\n \n\n\n\n In AIAA 2000-2357, pages 19–22, 2000. \n ISSN: 2000-2357\n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{yanta2000b,\n\ttitle = {Near- and farfield measurements of aero-optical effects due to propagation through hypersonic flows},\n\tdoi = {10.2514/6.2000-2357},\n\tabstract = {A series of aero-optics tests was carried out at Mach 7 in the Hypervelocity Wind Tunnel 9 (Tunnel 9) at the Arnold Engineering Development Center (AEDC). The test bed used for the measurements consisted of two flat plates which had sapphire windows mounted in titanium frames. Aero-optic measurements included near-field phase and intensity measurements made with two wavefront sensors, far-field point spread functions made with an imaging camera, and high temporal frequency optical tilts (boresight error) made with an X-Y Detector. Ancillary measurements of pressure and heat transfer on the test-bed plates were aiso made. The aero-optic measurements resulted in phase and intensity maps, boresight errors, contained energy diameters (CED's) and point spread functions (PSF's) that are associated with uncooled missile windows. Comparisons between the various measurements are made to ascertain aerodynamic effects, instrument errors, facility-induced errors, and measurement uncertainties.},\n\turldate = {2022-11-07},\n\tbooktitle = {{AIAA} 2000-2357},\n\tauthor = {Yanta, William J. and Spring, W. Charles and Neal, Daniel R. and Hamrick, Daniel R. and Copland, R. James and Lafferty, John F. and Collier, Arnold S. and Bell, Rita L. and Pezzaniti, Larry and Banish, Michele and Shaw, Russell},\n\tyear = {2000},\n\tnote = {ISSN: 2000-2357},\n\tpages = {19--22},\n}\n\n\n\n
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\n A series of aero-optics tests was carried out at Mach 7 in the Hypervelocity Wind Tunnel 9 (Tunnel 9) at the Arnold Engineering Development Center (AEDC). The test bed used for the measurements consisted of two flat plates which had sapphire windows mounted in titanium frames. Aero-optic measurements included near-field phase and intensity measurements made with two wavefront sensors, far-field point spread functions made with an imaging camera, and high temporal frequency optical tilts (boresight error) made with an X-Y Detector. Ancillary measurements of pressure and heat transfer on the test-bed plates were aiso made. The aero-optic measurements resulted in phase and intensity maps, boresight errors, contained energy diameters (CED's) and point spread functions (PSF's) that are associated with uncooled missile windows. Comparisons between the various measurements are made to ascertain aerodynamic effects, instrument errors, facility-induced errors, and measurement uncertainties.\n
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\n \n\n \n \n Yanta, W. J.; Spring, W. C.; Neal, D. R.; Hamrick, D. R.; Copland, R. J.; Lafferty, J. F.; Collier, A. S.; Bell, R. L.; Pezzaniti, L.; Banish, M.; and Shaw, R.\n\n\n \n \n \n \n Near- and farfield measurements of aero-optical effects due to propagation through hypersonic flows.\n \n \n \n\n\n \n\n\n\n In pages 19–22, 2000. \n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@inproceedings{yanta2000a,\n\ttitle = {Near- and farfield measurements of aero-optical effects due to propagation through hypersonic flows},\n\tdoi = {10.2514/6.2000-2357},\n\tabstract = {A series of aero-optics tests was carried out at Mach 7 in the Hypervelocity Wind Tunnel 9 (Tunnel 9) at the Arnold Engineering Development Center (AEDC). The test bed used for the measurements consisted of two flat plates which had sapphire windows mounted in titanium frames. Aero-optic measurements included near-field phase and intensity measurements made with two wavefront sensors, far-field point spread functions made with an imaging camera, and high temporal frequency optical tilts (boresight error) made with an X-Y Detector. Ancillary measurements of pressure and heat transfer on the test-bed plates were aiso made. The aero-optic measurements resulted in phase and intensity maps, boresight errors, contained energy diameters (CED's) and point spread functions (PSF's) that are associated with uncooled missile windows. Comparisons between the various measurements are made to ascertain aerodynamic effects, instrument errors, facility-induced errors, and measurement uncertainties.},\n\tauthor = {Yanta, William J. and Spring, W. Charles and Neal, Daniel R. and Hamrick, Daniel R. and Copland, R. James and Lafferty, John F. and Collier, Arnold S. and Bell, Rita L. and Pezzaniti, Larry and Banish, Michele and Shaw, Russell},\n\tyear = {2000},\n\tpages = {19--22},\n}\n\n\n\n
\n
\n\n\n
\n A series of aero-optics tests was carried out at Mach 7 in the Hypervelocity Wind Tunnel 9 (Tunnel 9) at the Arnold Engineering Development Center (AEDC). The test bed used for the measurements consisted of two flat plates which had sapphire windows mounted in titanium frames. Aero-optic measurements included near-field phase and intensity measurements made with two wavefront sensors, far-field point spread functions made with an imaging camera, and high temporal frequency optical tilts (boresight error) made with an X-Y Detector. Ancillary measurements of pressure and heat transfer on the test-bed plates were aiso made. The aero-optic measurements resulted in phase and intensity maps, boresight errors, contained energy diameters (CED's) and point spread functions (PSF's) that are associated with uncooled missile windows. Comparisons between the various measurements are made to ascertain aerodynamic effects, instrument errors, facility-induced errors, and measurement uncertainties.\n
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\n \n\n \n \n Yanta, W. J; Charles, W; Neal, D. R; Hamrick, D. R; Copland, R J.; Pezzaniti, L.; Banish, M.; Shaw, R.; and Yanta, W. J\n\n\n \n \n \n \n \n Near-and Farfield Measurements Of Aero-Optical Effects Due To Propagation Through Hypersonic Flows Near-and Farfield Measurements Of Aero-Optical Effects Due To Propagation Through Hypersonic Flows.\n \n \n \n \n\n\n \n\n\n\n In 2000. \n \n\n\n\n
\n\n\n\n \n \n \"Near-andPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{yanta2000,\n\ttitle = {Near-and {Farfield} {Measurements} {Of} {Aero}-{Optical} {Effects} {Due} {To} {Propagation} {Through} {Hypersonic} {Flows} {Near}-and {Farfield} {Measurements} {Of} {Aero}-{Optical} {Effects} {Due} {To} {Propagation} {Through} {Hypersonic} {Flows}},\n\turl = {http://arc.aiaa.org},\n\tdoi = {10.2514/6.2000-2357},\n\tabstract = {A series of aero-optics tests was carried out at Mach 7 in the Hypervelocity Wind Tunnel 9 (Tunnel 9) at the Arnold Engineering Development Center (AEDC). The test bed used for the measurements consisted of two flat plates which had sapphire windows mounted in titanium frames. Aero-optic measurements included near-field phase and intensity measurements made with two wavefront sensors, far-field point spread functions made with an imaging camera, and high temporal frequency optical tilts (boresight error) made with an X-Y Detector. Ancillary measurements of pressure and heat transfer on the test-bed plates were also made. The aero-optic measurements resulted in phase and intensity maps, boresight errors, contained energy diameters (CED's) and point spread functions (PSF's) that are associated with uncooled missile windows. Comparisons between the various measurements are made to ascertain aerodynamic effects, instrument errors, facility-induced errors, and measurement uncertainties.},\n\tauthor = {Yanta, William J and Charles, W and Neal, Daniel R and Hamrick, Daniel R and Copland, R James and Pezzaniti, Larry and Banish, Michele and Shaw, Russell and Yanta, William J},\n\tyear = {2000},\n}\n\n\n\n
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\n A series of aero-optics tests was carried out at Mach 7 in the Hypervelocity Wind Tunnel 9 (Tunnel 9) at the Arnold Engineering Development Center (AEDC). The test bed used for the measurements consisted of two flat plates which had sapphire windows mounted in titanium frames. Aero-optic measurements included near-field phase and intensity measurements made with two wavefront sensors, far-field point spread functions made with an imaging camera, and high temporal frequency optical tilts (boresight error) made with an X-Y Detector. Ancillary measurements of pressure and heat transfer on the test-bed plates were also made. The aero-optic measurements resulted in phase and intensity maps, boresight errors, contained energy diameters (CED's) and point spread functions (PSF's) that are associated with uncooled missile windows. Comparisons between the various measurements are made to ascertain aerodynamic effects, instrument errors, facility-induced errors, and measurement uncertainties.\n
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\n \n\n \n \n Stefanov, S. K.; Boyd, I. D.; and Cai, C. P.\n\n\n \n \n \n \n \n Monte Carlo analysis of macroscopic fluctuations in a rarefied hypersonic flow around a cylinder.\n \n \n \n \n\n\n \n\n\n\n Physics of Fluids, 12(5): 1226–1226. April 2000.\n Publisher: American Institute of PhysicsAIP\n\n\n\n
\n\n\n\n \n \n \"MontePaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{stefanov2000,\n\ttitle = {Monte {Carlo} analysis of macroscopic fluctuations in a rarefied hypersonic flow around a cylinder},\n\tvolume = {12},\n\turl = {https://aip.scitation.org/doi/abs/10.1063/1.870372},\n\tdoi = {10.1063/1.870372},\n\tabstract = {From consideration of the length scales characteristic of molecular and turbulent phenomena, it is proposed that flow instabilities and structural motions should be generated under certain rarefied...},\n\tnumber = {5},\n\tjournal = {Physics of Fluids},\n\tauthor = {Stefanov, Stefan K. and Boyd, Iain D. and Cai, Chun Pei},\n\tmonth = apr,\n\tyear = {2000},\n\tnote = {Publisher: American Institute of PhysicsAIP},\n\tkeywords = {Knudsen flow, Mach number, Monte Carlo methods, flow instability, flow simulation, fluctuations, hypersonic flow, rarefied fluid dynamics, vortices, wakes},\n\tpages = {1226--1226},\n}\n\n\n\n
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\n From consideration of the length scales characteristic of molecular and turbulent phenomena, it is proposed that flow instabilities and structural motions should be generated under certain rarefied...\n
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\n \n\n \n \n Barbato, M.; Reggiani, S.; Bruno, C.; and Muylaert, J.\n\n\n \n \n \n \n \n Model for Heterogeneous Catalysis on Metal Surfaces with Applications to Hypersonic Flows.\n \n \n \n \n\n\n \n\n\n\n Journal of Thermophysics and Heat Transfer, 14(3): 412–420. May 2000.\n Publisher: AIAA\n\n\n\n
\n\n\n\n \n \n \"ModelPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
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@article{barbato2000,\n\ttitle = {Model for {Heterogeneous} {Catalysis} on {Metal} {Surfaces} with {Applications} to {Hypersonic} {Flows}},\n\tvolume = {14},\n\turl = {https://arc.aiaa.org/doi/abs/10.2514/2.6539},\n\tdoi = {10.2514/2.6539},\n\tabstract = {A model for heterogeneous catalysis for copper, nickel, and platinum has been devised. The model simulates the heterogeneous chemical kinetics of dissociated airflow impinging metal surfaces. Elementary phenomena such as atomic and molecular adsorption, Eley-Rideal and Langmuir-Hinshelwood recombinations, and thermal desorption have been accounted for. Comparisons with experimental results for nitrogen and oxygen recombination show good agreement. The finite rate catalysis model has been used to analyze numerically the problems of heterogeneous catalysis similarity between hypersonic ground testing and reentry flight. Therefore, the flow around a blunt cone under these conditions has been calculated, and results for heat fluxes and for a suggested similarity parameter have been compared and discussed.},\n\tnumber = {3},\n\tjournal = {Journal of Thermophysics and Heat Transfer},\n\tauthor = {Barbato, M. and Reggiani, S. and Bruno, C. and Muylaert, J.},\n\tmonth = may,\n\tyear = {2000},\n\tnote = {Publisher: AIAA},\n\tkeywords = {Activation Energy, Boltzmann Constant, Freestream Conditions, Heterogeneous Catalysis, Heterogeneous Chemical Kinetics, Hypersonic Flows, Melting Points, Numerical Simulation, Thermal Protection System, Wind Tunnel Tests},\n\tpages = {412--420},\n}\n\n\n\n
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\n A model for heterogeneous catalysis for copper, nickel, and platinum has been devised. The model simulates the heterogeneous chemical kinetics of dissociated airflow impinging metal surfaces. Elementary phenomena such as atomic and molecular adsorption, Eley-Rideal and Langmuir-Hinshelwood recombinations, and thermal desorption have been accounted for. Comparisons with experimental results for nitrogen and oxygen recombination show good agreement. The finite rate catalysis model has been used to analyze numerically the problems of heterogeneous catalysis similarity between hypersonic ground testing and reentry flight. Therefore, the flow around a blunt cone under these conditions has been calculated, and results for heat fluxes and for a suggested similarity parameter have been compared and discussed.\n
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\n \n\n \n \n Jawahar, P; and Kamath, H.\n\n\n \n \n \n \n A High-Resolution Procedure for Eulerand Navier–Stokes Computationson Unstructured Grids.\n \n \n \n\n\n \n\n\n\n Journal of Computational Physics, 164(1): 165–203. 2000.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{jawahar2000,\n\ttitle = {A {High}-{Resolution} {Procedure} for {Eulerand} {Navier}--{Stokes} {Computationson} {Unstructured} {Grids}},\n\tvolume = {164},\n\tnumber = {1},\n\tjournal = {Journal of Computational Physics},\n\tauthor = {Jawahar, P and Kamath, Hement},\n\tyear = {2000},\n\tpages = {165--203},\n}\n\n\n\n
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\n
\n  \n 1999\n \n \n (3)\n \n \n
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\n \n \n
\n \n\n \n \n Xu, Y.; Cheng, L.; and Zhang, L.\n\n\n \n \n \n \n Carbon/silicon carbide composites prepared by chemical vapor infiltration combined with silicon melt infiltration.\n \n \n \n\n\n \n\n\n\n Carbon, 37(8): 1179–1187. January 1999.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{xu_carbonsilicon_1999,\n\ttitle = {Carbon/silicon carbide composites prepared by chemical vapor infiltration combined with silicon melt infiltration},\n\tvolume = {37},\n\tissn = {0008-6223},\n\tdoi = {10.1016/S0008-6223(98)00310-8},\n\tabstract = {In order to reduce processing costs and improve the thermal stability of three-dimensional carbon fiber-reinforced silicon carbide composites, a chemical vapor infiltration combined with silicon melt infiltration method was developed for fabricating composites. According to the size of the pores in the preform, chemical vapor infiltration (CVI) and silicon melt infiltration (SMI) were mainly used to infiltrate small pores between fibers in a bundle and large pores between bundles, respectively. In the chemical vapor infiltration process, a pyrolytic carbon interfacial layer and a silicon carbide barrier layer were deposited on the surface of the carbon fiber. Then the pre-coated preform was infiltrated with pitch which was pyrolysed to form a porous carbon matrix in the pores. Finally, the preform was infiltrated with silicon melt to obtain composites. The influence of the interface thickness on the mechanical properties and the failure behavior of the composites were investigated, and the optimum thickness of the pyrolytic carbon layer was obtained. Experimental results also revealed that CVI+SMI composites exhibited good thermal stability of the mechanical properties and failure behaviors after the composites were annealed at high temperatures.},\n\tnumber = {8},\n\turldate = {2023-10-30},\n\tjournal = {Carbon},\n\tauthor = {Xu, Yongdong and Cheng, Laifei and Zhang, Litong},\n\tmonth = jan,\n\tyear = {1999},\n\tkeywords = {A. Carbon/composites, B. Chemical vapor infiltration, D. Microstructure, Mechanical properties},\n\tpages = {1179--1187},\n}\n\n\n\n
\n
\n\n\n
\n In order to reduce processing costs and improve the thermal stability of three-dimensional carbon fiber-reinforced silicon carbide composites, a chemical vapor infiltration combined with silicon melt infiltration method was developed for fabricating composites. According to the size of the pores in the preform, chemical vapor infiltration (CVI) and silicon melt infiltration (SMI) were mainly used to infiltrate small pores between fibers in a bundle and large pores between bundles, respectively. In the chemical vapor infiltration process, a pyrolytic carbon interfacial layer and a silicon carbide barrier layer were deposited on the surface of the carbon fiber. Then the pre-coated preform was infiltrated with pitch which was pyrolysed to form a porous carbon matrix in the pores. Finally, the preform was infiltrated with silicon melt to obtain composites. The influence of the interface thickness on the mechanical properties and the failure behavior of the composites were investigated, and the optimum thickness of the pyrolytic carbon layer was obtained. Experimental results also revealed that CVI+SMI composites exhibited good thermal stability of the mechanical properties and failure behaviors after the composites were annealed at high temperatures.\n
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\n \n\n \n \n Gnoffo, P. A\n\n\n \n \n \n \n Planetary-Entry Gas Dynamics.\n \n \n \n\n\n \n\n\n\n Annual Review of Fluid Mechanics, 31. 1999.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{gnoffo1999,\n\ttitle = {Planetary-{Entry} {Gas} {Dynamics}},\n\tvolume = {31},\n\tdoi = {10.1146/annurev.fluid.31.1.459},\n\tjournal = {Annual Review of Fluid Mechanics},\n\tauthor = {Gnoffo, Peter A},\n\tyear = {1999},\n}\n\n\n\n
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\n \n\n \n \n Choquet, I.\n\n\n \n \n \n \n \n A new approach to model and simulate numerically surface chemistry in rarefied flows.\n \n \n \n \n\n\n \n\n\n\n Physics of Fluids, 11(6). May 1999.\n Publisher: American Institute of PhysicsAIP\n\n\n\n
\n\n\n\n \n \n \"APaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{choquet1999,\n\ttitle = {A new approach to model and simulate numerically surface chemistry in rarefied flows},\n\tvolume = {11},\n\tissn = {10.1063/1.870025},\n\turl = {https://aip.scitation.org/doi/abs/10.1063/1.870025},\n\tdoi = {10.1063/1.870025},\n\tabstract = {A new approach is proposed to model and simulate numerically surface chemistry within the frame of rarefied gas flows. It is developed to satisfy all together the following points: (i) describe the...},\n\tnumber = {6},\n\tjournal = {Physics of Fluids},\n\tauthor = {Choquet, Isabelle},\n\tmonth = may,\n\tyear = {1999},\n\tnote = {Publisher: American Institute of PhysicsAIP},\n\tkeywords = {Laplace transforms, catalysis, chemical equilibrium, chemically reactive flow, chemisorption, nonequilibrium flow, numerical analysis, rarefied fluid dynamics, surface chemistry},\n}\n\n\n\n
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\n A new approach is proposed to model and simulate numerically surface chemistry within the frame of rarefied gas flows. It is developed to satisfy all together the following points: (i) describe the...\n
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\n  \n 1998\n \n \n (10)\n \n \n
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\n \n\n \n \n Nedospasov, A. V.; and Bezlyudny, I. V.\n\n\n \n \n \n \n Hot Spot Formation on different Tokamak Wall Materials.\n \n \n \n\n\n \n\n\n\n Contributions to Plasma Physics, 38(1-2): 337–342. 1998.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{nedospasov1998,\n\ttitle = {Hot {Spot} {Formation} on different {Tokamak} {Wall} {Materials}},\n\tvolume = {38},\n\tcopyright = {Copyright © 1998 WILEY-VCH Verlag GmbH \\& Co. KGaA},\n\tissn = {1521-3986},\n\tdoi = {10.1002/ctpp.2150380151},\n\tabstract = {The thermal contraction phenomenon and generation of ‘hot spots’ due to thermoemission were described in [1–3]. The paper consider non-linear stages of heat contraction on the graphite, beryllium, tungsten and vanadium wall. It is shown that on the beryllium surface hot spot can't appear due to strong cooling by sublimation. For other materials the conditions of hot spot appearance due to local superheating of the wall have been calculated and their parameters were found: critical surface temperature, size of spots and their temperature profiles, heat fluxes from plasma to the spots. It have been calculated fluxes of sublimating materials from spots to the plasma. It is noticed that nominal temperature of the grafite divertor plate, accepted in ITER's project to being equal 1500°C, is lower then critical temperature of the development heat contraction due to thermoemission.},\n\tlanguage = {en},\n\tnumber = {1-2},\n\turldate = {2024-04-24},\n\tjournal = {Contributions to Plasma Physics},\n\tauthor = {Nedospasov, A. V. and Bezlyudny, I. V.},\n\tyear = {1998},\n\tpages = {337--342},\n}\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n
\n
\n\n\n
\n The thermal contraction phenomenon and generation of ‘hot spots’ due to thermoemission were described in [1–3]. The paper consider non-linear stages of heat contraction on the graphite, beryllium, tungsten and vanadium wall. It is shown that on the beryllium surface hot spot can't appear due to strong cooling by sublimation. For other materials the conditions of hot spot appearance due to local superheating of the wall have been calculated and their parameters were found: critical surface temperature, size of spots and their temperature profiles, heat fluxes from plasma to the spots. It have been calculated fluxes of sublimating materials from spots to the plasma. It is noticed that nominal temperature of the grafite divertor plate, accepted in ITER's project to being equal 1500°C, is lower then critical temperature of the development heat contraction due to thermoemission.\n
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\n \n\n \n \n Commitee, C. F. D.\n\n\n \n \n \n \n \n Guide: Guide for the Verification and Validation of Computational Fluid Dynamics Simulations (AIAA G-077-1998(2002)).\n \n \n \n \n\n\n \n\n\n\n In Washington, DC, 1998. American Institute of Aeronautics and Astronautics, Inc.\n \n\n\n\n
\n\n\n\n \n \n \"Guide:Paper\n  \n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{computationalfluiddynamicscommitee1998,\n\taddress = {Washington, DC},\n\ttitle = {Guide: {Guide} for the {Verification} and {Validation} of {Computational} {Fluid} {Dynamics} {Simulations} ({AIAA} {G}-077-1998(2002))},\n\tshorttitle = {Guide},\n\turl = {10.2514/4.472855},\n\turldate = {2024-03-27},\n\tpublisher = {American Institute of Aeronautics and Astronautics, Inc.},\n\tauthor = {Computational Fluid Dynamics Commitee},\n\tyear = {1998},\n}\n\n\n\n\n\n\n\n
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\n \n\n \n \n Davis, J.\n\n\n \n \n \n \n Metals Handbook Desk Edition.\n \n \n \n\n\n \n\n\n\n ASM International, 2nd edition, 1998.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@book{davis_metals_1998,\n\tedition = {2nd},\n\ttitle = {Metals {Handbook} {Desk} {Edition}},\n\tpublisher = {ASM International},\n\tauthor = {Davis, Joseph},\n\tyear = {1998},\n}\n\n\n\n
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\n\n\n
\n \n\n \n \n Adamovich, I. V; Macheret, S. O; Rich, J W.; and Treanor, C. E\n\n\n \n \n \n \n Vibrational Energy Transfer Rates Using a Forced Harmonic Oscillator Model.\n \n \n \n\n\n \n\n\n\n Journal of Thermophysics and Heat Transfer, 12(1): 57–65. 1998.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{adamovich1998,\n\ttitle = {Vibrational {Energy} {Transfer} {Rates} {Using} a {Forced} {Harmonic} {Oscillator} {Model}},\n\tvolume = {12},\n\tnumber = {1},\n\tjournal = {Journal of Thermophysics and Heat Transfer},\n\tauthor = {Adamovich, Igor V and Macheret, Sergery O and Rich, J William and Treanor, Charles E},\n\tyear = {1998},\n\tpages = {57--65},\n}\n\n\n\n
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\n \n\n \n \n Aftosmis, M. J.; Berger, M. J.; and Melton, J. E.\n\n\n \n \n \n \n Robust and efficient Cartesian mesh generation for component-based geometry.\n \n \n \n\n\n \n\n\n\n AIAA Journal, 36(6): 952–960. May 1998.\n Publisher: American Institute of Aeronautics and Astronautics Inc.\n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{aftosmis1998,\n\ttitle = {Robust and efficient {Cartesian} mesh generation for component-based geometry},\n\tvolume = {36},\n\tdoi = {10.2514/2.464},\n\tabstract = {This work documents a new method for rapid and robust Cartesian mesh generation for component-based geometry. The new algorithm adopts a novel strategy that first intersects the components to extract the wetted surface before proceeding with volume mesh generation in a second phase. The intersection scheme is based on a robust geometry engine that uses adaptive precision arithmetic and automatically and consistently handles geometric degeneracies with an algorithmic tie-breaking routine. The intersection procedure has worst-case computational complexity of O(N log N) and is demonstrated on test cases with up to 121 overlapping and intersecting components, including a variety of geometric degeneracies. The volume mesh generation takes the intersected surface triangulation as input and generates the mesh through cell division of an initially uniform coarse grid. In refining hexagonal cells to resolve the geometry, the new approach preserves the ability to directionally divide cells that are well aligned with local geometry. The mesh generation scheme has linear asymptotic complexity with memory requirements that total approximately 14-17 words/cell. The mesh generation speed is approximately 106 cells/minute on a typical engineering workstation.},\n\tnumber = {6},\n\tjournal = {AIAA Journal},\n\tauthor = {Aftosmis, M. J. and Berger, M. J. and Melton, J. E.},\n\tmonth = may,\n\tyear = {1998},\n\tnote = {Publisher: American Institute of Aeronautics and Astronautics Inc.},\n\tkeywords = {Computer Aided Design, Computing, Fuselages, Hardware Development, Helicopters, High Aspect Ratio, High Speed Civil Transport, Institute of Electrical and Electronics Engineers, Mesh Generation, Recursive Algorithm},\n\tpages = {952--960},\n}\n\n\n\n
\n
\n\n\n
\n This work documents a new method for rapid and robust Cartesian mesh generation for component-based geometry. The new algorithm adopts a novel strategy that first intersects the components to extract the wetted surface before proceeding with volume mesh generation in a second phase. The intersection scheme is based on a robust geometry engine that uses adaptive precision arithmetic and automatically and consistently handles geometric degeneracies with an algorithmic tie-breaking routine. The intersection procedure has worst-case computational complexity of O(N log N) and is demonstrated on test cases with up to 121 overlapping and intersecting components, including a variety of geometric degeneracies. The volume mesh generation takes the intersected surface triangulation as input and generates the mesh through cell division of an initially uniform coarse grid. In refining hexagonal cells to resolve the geometry, the new approach preserves the ability to directionally divide cells that are well aligned with local geometry. The mesh generation scheme has linear asymptotic complexity with memory requirements that total approximately 14-17 words/cell. The mesh generation speed is approximately 106 cells/minute on a typical engineering workstation.\n
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\n \n\n \n \n Sutton, K.; and Gnoffo, P. A\n\n\n \n \n \n \n Multi-Component Diffusion with Application To Computational Aerothermodynamics.\n \n \n \n\n\n \n\n\n\n In Albuquerque, NM, 1998. \\AIAA Paper\\ 1998-2575\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{sutton1998,\n\taddress = {Albuquerque, NM},\n\ttitle = {Multi-{Component} {Diffusion} with {Application} {To} {Computational} {Aerothermodynamics}},\n\tpublisher = {\\{AIAA Paper\\} 1998-2575},\n\tauthor = {Sutton, Kenneth and Gnoffo, Peter A},\n\tyear = {1998},\n}\n\n\n\n
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\n \n\n \n \n Shimura, T.; Mitani, T.; Sakuranaka, N.; and Izumikawa, M.\n\n\n \n \n \n \n \n Load Oscillations Caused by Unstart of Hypersonic Wind Tunnels and Engines.\n \n \n \n \n\n\n \n\n\n\n Journal of Propulsion and Power, 14(3). 1998.\n \n\n\n\n
\n\n\n\n \n \n \"LoadPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{shimura1998,\n\ttitle = {Load {Oscillations} {Caused} by {Unstart} of {Hypersonic} {Wind} {Tunnels} and {Engines}},\n\tvolume = {14},\n\turl = {http://arc.aiaa.org},\n\tdoi = {10.2514/2.5287},\n\tabstract = {Large-amplitude load oscillations were observed during the tests of a hypersonic engine model in a freejet-type wind tunnel. To clarify the cause of the oscillations and their characteristics, oscillating wall pressures and loads on a drag model and engine models were investigated. Floww eld was observed by shadowgraph to determine the cause of the large starting loads. Power spectral density functions and probability functions of wall pressures and loads were derived by the fast Fourier transform. The amplitude of the unsteady frontal pressure was correlated with the dynamic pressure. The magnitude of the starting load was related to the drag coeff cient of the models, and the expected maximum peak loads of a large-scale ramjet engine test facility were evaluated. Engine unstart loads were also simulated by means of secondary ow injection into a small-scale model of a ramjet engine. With these methods, characteristics of engine unstart loads and the possibility of sensing engine unstart in its early phase were studied. Engine unstart could be sensed with pressure measurement around the engine throat before it became severe. Furthermore, engine unstart loads associated with scramjet engine combustion were related to the drag coeff cient of the engine. Nomenclature A f = frontal area of test piece C d = drag coeff cient, F d /Af/q C dp = peak load coeff cient, F u /Af/q F d = drag without fuel injection F p = pressure drag, A f P 20 F u = peak value of unsteady loads caused by unstart of engines or wind tunnels M = Mach number P(x) = cumulative probability distribution function, time interval with X AC x in total sampling time, Prob\\{XAC x\\} P 0 = nozzle total pressure P 20 = frontal pressure, pitot pressure q = dynamic pressure of freejet X ¯ = mean value of X(t) X AC = X(t) X ¯ X(t) = time-dependent sample functions = standard deviation of X AC},\n\tnumber = {3},\n\tjournal = {Journal of Propulsion and Power},\n\tauthor = {Shimura, Takashi and Mitani, Tohru and Sakuranaka, Noboru and Izumikawa, Muneo},\n\tyear = {1998},\n}\n\n\n\n
\n
\n\n\n
\n Large-amplitude load oscillations were observed during the tests of a hypersonic engine model in a freejet-type wind tunnel. To clarify the cause of the oscillations and their characteristics, oscillating wall pressures and loads on a drag model and engine models were investigated. Floww eld was observed by shadowgraph to determine the cause of the large starting loads. Power spectral density functions and probability functions of wall pressures and loads were derived by the fast Fourier transform. The amplitude of the unsteady frontal pressure was correlated with the dynamic pressure. The magnitude of the starting load was related to the drag coeff cient of the models, and the expected maximum peak loads of a large-scale ramjet engine test facility were evaluated. Engine unstart loads were also simulated by means of secondary ow injection into a small-scale model of a ramjet engine. With these methods, characteristics of engine unstart loads and the possibility of sensing engine unstart in its early phase were studied. Engine unstart could be sensed with pressure measurement around the engine throat before it became severe. Furthermore, engine unstart loads associated with scramjet engine combustion were related to the drag coeff cient of the engine. Nomenclature A f = frontal area of test piece C d = drag coeff cient, F d /Af/q C dp = peak load coeff cient, F u /Af/q F d = drag without fuel injection F p = pressure drag, A f P 20 F u = peak value of unsteady loads caused by unstart of engines or wind tunnels M = Mach number P(x) = cumulative probability distribution function, time interval with X AC x in total sampling time, Prob\\XAC x\\ P 0 = nozzle total pressure P 20 = frontal pressure, pitot pressure q = dynamic pressure of freejet X ¯ = mean value of X(t) X AC = X(t) X ¯ X(t) = time-dependent sample functions = standard deviation of X AC\n
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\n \n\n \n \n Okuma, M.; and Oho, T.\n\n\n \n \n \n \n Experimental Spatial Matrix Identification as a Practical Inverse Problem in Mechanics.\n \n \n \n\n\n \n\n\n\n In Olson, L. G.; and Saigal, S., editor(s), Computational Methods for Solution of Inverse Problems in Mechanics. ASME, New York, 1998.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@incollection{okuma1998,\n\taddress = {New York},\n\ttitle = {Experimental {Spatial} {Matrix} {Identification} as a {Practical} {Inverse} {Problem} in {Mechanics}},\n\tbooktitle = {Computational {Methods} for {Solution} of {Inverse} {Problems} in {Mechanics}},\n\tpublisher = {ASME},\n\tauthor = {Okuma, M. and Oho, T.},\n\teditor = {Olson, L. G. and Saigal, S.},\n\tyear = {1998},\n}\n\n\n\n
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\n \n\n \n \n Schwenke, D. W.\n\n\n \n \n \n \n Calculations of rate constants for the three‐body recombination of H2 in the presence of H2.\n \n \n \n\n\n \n\n\n\n The Journal of Chemical Physics, 89(4): 2076–2076. August 1998.\n Publisher: American Institute of PhysicsAIP\n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{schwenke1998,\n\ttitle = {Calculations of rate constants for the three‐body recombination of {H2} in the presence of {H2}},\n\tvolume = {89},\n\tdoi = {10.1063/1.455104},\n\tabstract = {We construct a new global potential energy hypersurface for H2+H2 and perform quasiclassical trajectory calculations using the resonance complex theory and energy transfer mechanism to estimate the...},\n\tnumber = {4},\n\tjournal = {The Journal of Chemical Physics},\n\tauthor = {Schwenke, David W.},\n\tmonth = aug,\n\tyear = {1998},\n\tnote = {Publisher: American Institute of PhysicsAIP},\n\tkeywords = {CHEMICAL REACTION KINETICS, COMBUSTION, ENERGY TRANSFER, HIGH TEMPERATURE, HYDROGEN, LOW TEMPERATURE, MEDIUM TEMPERATURE, POTENTIALS, RECOMBINATION, ULTRAHIGH TEMPERATURE, VERY HIGH TEMPERATURE},\n\tpages = {2076--2076},\n}\n\n\n\n
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\n We construct a new global potential energy hypersurface for H2+H2 and perform quasiclassical trajectory calculations using the resonance complex theory and energy transfer mechanism to estimate the...\n
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\n \n\n \n \n Cao, X.; Sugiyama, Y.; and Mitsui, Y.\n\n\n \n \n \n \n Application of artificial neural networks to load identification.\n \n \n \n\n\n \n\n\n\n Computers & Structures, 69(1): 63–78. October 1998.\n Publisher: Pergamon\n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{cao1998,\n\ttitle = {Application of artificial neural networks to load identification},\n\tvolume = {69},\n\tdoi = {10.1016/S0045-7949(98)00085-6},\n\tabstract = {The intended aim of the study is to develope an approach to the identification of the loads acting on aircraft wings, which uses an artificial neural network to model the load-strain relationship in structural analysis. As the first step of the study, this paper describes the application of an artificial neural network to identify the loads distributed across a cantilevered beam. The distributed loads are approximated by a set of concentrated loads. The paper demonstrates that using an artificial neural network to identify loads is feasible and a well trained artificial neural network reveals an extremely fast convergence and a high degree of accuracy in the process of load identification for a cantilevered beam model. © 1998 Elsevier Science Ltd. All rights reserved.},\n\tnumber = {1},\n\tjournal = {Computers \\& Structures},\n\tauthor = {Cao, X. and Sugiyama, Y. and Mitsui, Y.},\n\tmonth = oct,\n\tyear = {1998},\n\tnote = {Publisher: Pergamon},\n\tkeywords = {Artificial neural network, Inverse problem, Load identification},\n\tpages = {63--78},\n}\n\n\n\n
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\n The intended aim of the study is to develope an approach to the identification of the loads acting on aircraft wings, which uses an artificial neural network to model the load-strain relationship in structural analysis. As the first step of the study, this paper describes the application of an artificial neural network to identify the loads distributed across a cantilevered beam. The distributed loads are approximated by a set of concentrated loads. The paper demonstrates that using an artificial neural network to identify loads is feasible and a well trained artificial neural network reveals an extremely fast convergence and a high degree of accuracy in the process of load identification for a cantilevered beam model. © 1998 Elsevier Science Ltd. All rights reserved.\n
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\n  \n 1997\n \n \n (8)\n \n \n
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\n \n\n \n \n Golecki, I.\n\n\n \n \n \n \n \n Rapid vapor-phase densification of refractory composites.\n \n \n \n \n\n\n \n\n\n\n Materials Science and Engineering: R: Reports, 20(2): 37–124. June 1997.\n \n\n\n\n
\n\n\n\n \n \n \"RapidPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{golecki_rapid_1997,\n\tseries = {R20},\n\ttitle = {Rapid vapor-phase densification of refractory composites},\n\tvolume = {20},\n\tissn = {0927-796X},\n\turl = {https://www.sciencedirect.com/science/article/pii/S0927796X9700003X},\n\tdoi = {10.1016/S0927-796X(97)00003-X},\n\tabstract = {The status of vapor-phase routes for the rapid densification of high-temperature composite materials, primarily ceramic-matrix composites, is reviewed. Conventional densification of composites such as carbon-carbon and SiC-SiC is accomplished by isothermal, isobaric chemical vapor infiltration (CVI), either alone or in combination with liquid resin impregnation and thermal annealing. These are multi-step processes which take from several hundred to thousands of hours at high temperature. In this paper we review approaches designed to significantly reduce the processing time and the number of steps required for densification, while producing materials with the desired properties. We describe techniques such as inductively-heated thermal-gradient isobaric CVI, radiantly-heated isothermal and thermal-gradient forced-flow CVI, liquid-immersion thermal-gradient CVI and plasma-enhanced CVI. Different heating methods, such as radiative and inductive, and both hot-wall and cold-wall reactors are compared. Available material properties of composites produced by these techniques are given.},\n\tnumber = {2},\n\turldate = {2023-10-30},\n\tjournal = {Materials Science and Engineering: R: Reports},\n\tauthor = {Golecki, I.},\n\tmonth = jun,\n\tyear = {1997},\n\tkeywords = {Carbon-carbon composites, Ceramic-matrix composites, Chemical vapor deposition, Chemical vapor infiltration, Composites, Densification, Fiber, Forced flow, High-temperature composites, Inductive heating, Isobaric, Isothermal, Liquid immersion, Matrix, Microwave, Plasma, Preform, Pulsed pressure, Radiant heating, Rapid densification, SiC-SiC, Thermal gradient},\n\tpages = {37--124},\n}\n\n\n\n
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\n The status of vapor-phase routes for the rapid densification of high-temperature composite materials, primarily ceramic-matrix composites, is reviewed. Conventional densification of composites such as carbon-carbon and SiC-SiC is accomplished by isothermal, isobaric chemical vapor infiltration (CVI), either alone or in combination with liquid resin impregnation and thermal annealing. These are multi-step processes which take from several hundred to thousands of hours at high temperature. In this paper we review approaches designed to significantly reduce the processing time and the number of steps required for densification, while producing materials with the desired properties. We describe techniques such as inductively-heated thermal-gradient isobaric CVI, radiantly-heated isothermal and thermal-gradient forced-flow CVI, liquid-immersion thermal-gradient CVI and plasma-enhanced CVI. Different heating methods, such as radiative and inductive, and both hot-wall and cold-wall reactors are compared. Available material properties of composites produced by these techniques are given.\n
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\n \n\n \n \n Chang, C.; Vinh, H.; Malik, M.; Malik, M.; Chang, C.; and Vinh, H.\n\n\n \n \n \n \n Hypersonic boundary-layer stability with chemical reactions using PSE.\n \n \n \n\n\n \n\n\n\n In 28th Fluid Dynamics Conference, Snowmass Village,CO,U.S.A., June 1997. AIAA Paper 1997-2012\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{chang1997,\n\taddress = {Snowmass Village,CO,U.S.A.},\n\ttitle = {Hypersonic boundary-layer stability with chemical reactions using {PSE}},\n\tdoi = {10.2514/6.1997-2012},\n\tlanguage = {en},\n\turldate = {2023-08-08},\n\tbooktitle = {28th {Fluid} {Dynamics} {Conference}},\n\tpublisher = {AIAA Paper 1997-2012},\n\tauthor = {Chang, C.-L. and Vinh, H. and Malik, M. and Malik, M. and Chang, C.-L. and Vinh, H.},\n\tmonth = jun,\n\tyear = {1997},\n}\n\n\n\n\n\n\n\n
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\n \n\n \n \n Bose, D.; and Candler, G. V\n\n\n \n \n \n \n \n Thermal rate constants of the O2+N→NO+O reaction based on the A2′ and A4′ potential-energy surfaces.\n \n \n \n \n\n\n \n\n\n\n The Journal of Chemical Physics, 107(16): 6136–6145. 1997.\n \n\n\n\n
\n\n\n\n \n \n \"ThermalPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{bose1997,\n\ttitle = {Thermal rate constants of the {O2}+{N}→{NO}+{O} reaction based on the {A2}′ and {A4}′ potential-energy surfaces},\n\tvolume = {107},\n\turl = {https://doi.org/10.1063/1.475132},\n\tdoi = {10.1063/1.475132},\n\tnumber = {16},\n\tjournal = {The Journal of Chemical Physics},\n\tauthor = {Bose, Deepak and Candler, Graham V},\n\tyear = {1997},\n\tpages = {6136--6145},\n}\n\n\n\n
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\n \n\n \n \n Karypis, G.; and Kumar, V.\n\n\n \n \n \n \n METIS: A Software Package for Partitioning Unstructured Graphs, Partitioning Meshes, and Computing Fill-Reducing Orderings of Sparse Matrices.\n \n \n \n\n\n \n\n\n\n Technical Report 1997.\n Issue: 97-061\n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@techreport{karypis1997,\n\ttitle = {{METIS}: {A} {Software} {Package} for {Partitioning} {Unstructured} {Graphs}, {Partitioning} {Meshes}, and {Computing} {Fill}-{Reducing} {Orderings} of {Sparse} {Matrices}},\n\tauthor = {Karypis, George and Kumar, Vipin},\n\tyear = {1997},\n\tnote = {Issue: 97-061},\n}\n\n\n\n
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\n \n\n \n \n Lide, D R\n\n\n \n \n \n \n Handbook of Chemistry and Physics.\n \n \n \n\n\n \n\n\n\n CRC Press, Boca Raton, 78th edition, 1997.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@book{lide1997,\n\taddress = {Boca Raton},\n\tedition = {78th},\n\ttitle = {Handbook of {Chemistry} and {Physics}},\n\tpublisher = {CRC Press},\n\tauthor = {Lide, D R},\n\tyear = {1997},\n}\n\n\n\n
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\n \n\n \n \n Adam, P. H; and Hornung, H. G\n\n\n \n \n \n \n \n Enthalpy Effects on Hypervelocity Boundary-Layer Transition: Ground Test and Flight Data.\n \n \n \n \n\n\n \n\n\n\n Journal of Spacecraft and Rockets, 34(5). 1997.\n \n\n\n\n
\n\n\n\n \n \n \"EnthalpyPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{adam1997,\n\ttitle = {Enthalpy {Effects} on {Hypervelocity} {Boundary}-{Layer} {Transition}: {Ground} {Test} and {Flight} {Data}},\n\tvolume = {34},\n\turl = {http://arc.aiaa.org},\n\tdoi = {10.2514/2.3278},\n\tabstract = {Boundary-layer-transitionexperiments on a 5-deg half-angle cone at 0-deg angle of attack were performed in the T5 hypervelocity shock tunnel. The test gases investigated included air, nitrogen, and carbon dioxide. Reservoir enthalpies were varied from 3 to 27 MJ/kg and reservoir pressures from 10 to 95 MPa, depending on the gas and tunnel settings. No clear relationship is found to exist between the transition Reynolds number based on the boundary-layer-edge conditions and the reservoir enthalpy. However, when the reference temperature conditions are used instead, the different test gases are distinguishable and ordered according to their dissociation energy. Data from a free-ight experiment are also compared with the shock tunnel experiments. When the transition Reynolds numbers are evaluated at the boundary-layer-edge conditions, they are an order of magnitude higher than the tunnel results. However, when the reference conditions are used, the ight data fall within the same range as the experiments, although the trend with reservoir enthalpy is reversed. Nomenclature h = enthalpy, MJ/kg M = Mach number P = pressure, Pa P q = heat transfer rate, MW/m 2 Re = Reynolds number r = recovery factor St = Stanton number T = temperature, K u = velocity, m/s x = axial distance, m ¹ = viscosity, kg/m-s ½ = density, kg/m 3 Subscripts a = adiabatic e = boundary-layer edge tr = transition w = wall 0 = reservoir 1 = freestream Superscript ¤ = reference condition},\n\tnumber = {5},\n\tjournal = {Journal of Spacecraft and Rockets},\n\tauthor = {Adam, Philippe H and Hornung, Hans G},\n\tyear = {1997},\n}\n\n\n\n
\n
\n\n\n
\n Boundary-layer-transitionexperiments on a 5-deg half-angle cone at 0-deg angle of attack were performed in the T5 hypervelocity shock tunnel. The test gases investigated included air, nitrogen, and carbon dioxide. Reservoir enthalpies were varied from 3 to 27 MJ/kg and reservoir pressures from 10 to 95 MPa, depending on the gas and tunnel settings. No clear relationship is found to exist between the transition Reynolds number based on the boundary-layer-edge conditions and the reservoir enthalpy. However, when the reference temperature conditions are used instead, the different test gases are distinguishable and ordered according to their dissociation energy. Data from a free-ight experiment are also compared with the shock tunnel experiments. When the transition Reynolds numbers are evaluated at the boundary-layer-edge conditions, they are an order of magnitude higher than the tunnel results. However, when the reference conditions are used, the ight data fall within the same range as the experiments, although the trend with reservoir enthalpy is reversed. Nomenclature h = enthalpy, MJ/kg M = Mach number P = pressure, Pa P q = heat transfer rate, MW/m 2 Re = Reynolds number r = recovery factor St = Stanton number T = temperature, K u = velocity, m/s x = axial distance, m ¹ = viscosity, kg/m-s ½ = density, kg/m 3 Subscripts a = adiabatic e = boundary-layer edge tr = transition w = wall 0 = reservoir 1 = freestream Superscript ¤ = reference condition\n
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\n \n\n \n \n Canuto, V. M.\n\n\n \n \n \n \n \n Compressible Turbulence.\n \n \n \n \n\n\n \n\n\n\n The Astrophysical Journal, 482(2): 827–827. June 1997.\n Publisher: IOP Publishing\n\n\n\n
\n\n\n\n \n \n \"CompressiblePaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n\n\n\n
\n 
@article{canuto1997,\n\ttitle = {Compressible {Turbulence}},\n\tvolume = {482},\n\turl = {https://iopscience.iop.org/article/10.1086/304175},\n\tdoi = {10.1086/304175},\n\tabstract = {We present a model to treat fully compressible, nonlocal, time-dependent turbulent convection in the presence of large-scale flows and arbitrary density stratification. The problem is of interest, for example, in stellar pulsation problems, especially since accurate helioseismological data are now available, as well as in accretion disks. Owing to the difficulties in formulating an analytical model, it is not surprising that most of the work has gone into numerical simulations. At present, there are three analytical models: one by the author, which leads to a rather complicated set of equations; one by Yoshizawa; and one by Xiong. The latter two use a Reynolds stress model together with phenomenological relations with adjustable parameters whose determination on the basis of terrestrial flows does not guarantee that they may be extrapolated to astrophysical flows. Moreover, all third-order moments representing nonlocality are taken to be of the down gradient form (which in the case of the planetary boundary layer yields incorrect results). In addition, correlations among pressure, temperature, and velocities are often neglected or treated as in the incompressible case. To avoid phenomenological relations, we derive the full set of dynamic, time-dependent, nonlocal equations to describe all mean variables, second- and third-order moments. Closures are carried out at the fourth order following standard procedures in turbulence modeling. The equations are collected in an Appendix. Some of the novelties of the treatment are (1) new flux conservation law that includes the large-scale flow, (2) increase of the rate of dissipation of turbulent kinetic energy owing to compressibility and thus (3) a smaller overshooting, and (4) a new source of mean temperature due to compressibility; moreover, contrary to some phenomenological suggestions, the adiabatic temperature gradient depends only on the thermal pressure, while in the equation for the large-scale flow, the physical pressure is the sum of thermal plus turbulent pressure.},\n\tnumber = {2},\n\tjournal = {The Astrophysical Journal},\n\tauthor = {Canuto, V. M.},\n\tmonth = jun,\n\tyear = {1997},\n\tnote = {Publisher: IOP Publishing},\n\tkeywords = {Subject headings, hydrodynamics È turbulence},\n\tpages = {827--827},\n}\n\n\n\n
\n
\n\n\n
\n We present a model to treat fully compressible, nonlocal, time-dependent turbulent convection in the presence of large-scale flows and arbitrary density stratification. The problem is of interest, for example, in stellar pulsation problems, especially since accurate helioseismological data are now available, as well as in accretion disks. Owing to the difficulties in formulating an analytical model, it is not surprising that most of the work has gone into numerical simulations. At present, there are three analytical models: one by the author, which leads to a rather complicated set of equations; one by Yoshizawa; and one by Xiong. The latter two use a Reynolds stress model together with phenomenological relations with adjustable parameters whose determination on the basis of terrestrial flows does not guarantee that they may be extrapolated to astrophysical flows. Moreover, all third-order moments representing nonlocality are taken to be of the down gradient form (which in the case of the planetary boundary layer yields incorrect results). In addition, correlations among pressure, temperature, and velocities are often neglected or treated as in the incompressible case. To avoid phenomenological relations, we derive the full set of dynamic, time-dependent, nonlocal equations to describe all mean variables, second- and third-order moments. Closures are carried out at the fourth order following standard procedures in turbulence modeling. The equations are collected in an Appendix. Some of the novelties of the treatment are (1) new flux conservation law that includes the large-scale flow, (2) increase of the rate of dissipation of turbulent kinetic energy owing to compressibility and thus (3) a smaller overshooting, and (4) a new source of mean temperature due to compressibility; moreover, contrary to some phenomenological suggestions, the adiabatic temperature gradient depends only on the thermal pressure, while in the equation for the large-scale flow, the physical pressure is the sum of thermal plus turbulent pressure.\n
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\n \n\n \n \n Baillion, M.\n\n\n \n \n \n \n \n Blunt Body Dynamic Derivatives.\n \n \n \n \n\n\n \n\n\n\n Technical Report 1997.\n \n\n\n\n
\n\n\n\n \n \n \"BluntPaper\n  \n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@techreport{baillion1997,\n\ttitle = {Blunt {Body} {Dynamic} {Derivatives}},\n\turl = {http://www.dtic.mil/ docs/citations/ADA326819.},\n\tauthor = {Baillion, M.},\n\tyear = {1997},\n}\n\n\n\n
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\n  \n 1996\n \n \n (5)\n \n \n
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\n \n\n \n \n Bose, D.; and Candler, G. V\n\n\n \n \n \n \n \n Thermal rate constants of the N2+O→NO+N reaction using ab initio 3A″ and 3A′ potential energy surfaces.\n \n \n \n \n\n\n \n\n\n\n The Journal of Chemical Physics, 104(8): 2825–2833. 1996.\n \n\n\n\n
\n\n\n\n \n \n \"ThermalPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{bose1996,\n\ttitle = {Thermal rate constants of the {N2}+{O}→{NO}+{N} reaction using ab initio {3A}″ and {3A}′ potential energy surfaces},\n\tvolume = {104},\n\turl = {https://doi.org/10.1063/1.471106},\n\tdoi = {10.1063/1.471106},\n\tnumber = {8},\n\tjournal = {The Journal of Chemical Physics},\n\tauthor = {Bose, Deepak and Candler, Graham V},\n\tyear = {1996},\n\tpages = {2825--2833},\n}\n\n\n\n
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\n \n\n \n \n Scott, R. C; and Pototzkyt, A. S\n\n\n \n \n \n \n \n Quasisteady Aerodynamics for Flutter Analysis Using Steady Computational Fluid Dynamics Calculations.\n \n \n \n \n\n\n \n\n\n\n Journal of Aircraft, 33(1). 1996.\n \n\n\n\n
\n\n\n\n \n \n \"QuasisteadyPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{scott1996,\n\ttitle = {Quasisteady {Aerodynamics} for {Flutter} {Analysis} {Using} {Steady} {Computational} {Fluid} {Dynamics} {Calculations}},\n\tvolume = {33},\n\turl = {http://arc.aiaa.org},\n\tdoi = {10.2514/3.46921},\n\tabstract = {A quasisteady method is presented where the results of steady computational fluid dynamics (CFD) calculations are used to obtain generalized aerodynamic forces for flutter analysis. For high-speed flows, the method provides a bridge between the computational efficiency, but relative, inaccuracies of piston theory and the greater accuracy, but high, computational cost of CFD flutter calculations. The method uses the structure's vibratory modes to modify the boundary conditions in the steady CFD calculations. Two steady CFD solutions are required per vibratory mode: one for the static part and one for the harmonic part of the pressure distribution. The pressure distributions of these solutions can be used to compute generalized aerodynamic forces necessary for flutter analysis. Sample two-and three-dimensional aerodynamic force calculations are provided demonstrating the method, and a flutter analysis of a National Aerospace Plane type wing is also discussed. Nomenclature A () = matrix of coefficients related to the static part of the generalized aerodynamic forces A, = matrix of coefficients related to the harmonic part of generalized aerodynamic forces b = wing semichord C p = pressure coefficient, (p-p x)/q d = arbitrary scale factor, q{\\textasciicircum}lV{\\textasciicircum} k = reduced frequency, a)b/V x p = pressure q = dynamic pressure, ip{\\textasciicircum}VJ qj = yth generalized coordinate qj = arbitrary scale factor used in calculation of static pressures for yth mode 4y = arbitrary scale factor used in calculation of harmonic pressures for yth mode Sj = surface grid contour deformed into yth mode shape S = surface grid contour t = time V = velocity W s = steady-state mass flux vector w = downwash x = x coordinate, origin at leading-edge root, positive aft y = y coordinate, origin at leading-edge root, positive spanwise Z = vertical deformation of surface Z () j = complex amplitude of yth mode Presented as Paper 93-1364 at the AIAA 34th Structures, Struc-z = z coordinate, origin at leading-edge root, positive up a = angle of attack p = density a = real part of eigenvalue {\\textless}/{\\textgreater}j = yth mode shape function {\\textless}l{\\textgreater}j = yth integrated mode shape function for calculating harmonic pressures (0-circular frequency Subscripts le = value of quantity at leading edge of wing or vehicle lower = value of quantity on lower surface of wing or vehicle ss = steady state or static aeroelastic value of quantity te = value of quantity at trailing edge of wing or vehicle upper = value of quantity on upper surface of wing or vehicle 3° = freestream value of quantity Superscripts I = harmonic part of quantity R = static part of quantity},\n\tnumber = {1},\n\tjournal = {Journal of Aircraft},\n\tauthor = {Scott, Robert C and Pototzkyt, Anthony S},\n\tyear = {1996},\n}\n\n\n\n
\n
\n\n\n
\n A quasisteady method is presented where the results of steady computational fluid dynamics (CFD) calculations are used to obtain generalized aerodynamic forces for flutter analysis. For high-speed flows, the method provides a bridge between the computational efficiency, but relative, inaccuracies of piston theory and the greater accuracy, but high, computational cost of CFD flutter calculations. The method uses the structure's vibratory modes to modify the boundary conditions in the steady CFD calculations. Two steady CFD solutions are required per vibratory mode: one for the static part and one for the harmonic part of the pressure distribution. The pressure distributions of these solutions can be used to compute generalized aerodynamic forces necessary for flutter analysis. Sample two-and three-dimensional aerodynamic force calculations are provided demonstrating the method, and a flutter analysis of a National Aerospace Plane type wing is also discussed. Nomenclature A () = matrix of coefficients related to the static part of the generalized aerodynamic forces A, = matrix of coefficients related to the harmonic part of generalized aerodynamic forces b = wing semichord C p = pressure coefficient, (p-p x)/q d = arbitrary scale factor, q\\textasciicircumlV\\textasciicircum k = reduced frequency, a)b/V x p = pressure q = dynamic pressure, ip\\textasciicircumVJ qj = yth generalized coordinate qj = arbitrary scale factor used in calculation of static pressures for yth mode 4y = arbitrary scale factor used in calculation of harmonic pressures for yth mode Sj = surface grid contour deformed into yth mode shape S = surface grid contour t = time V = velocity W s = steady-state mass flux vector w = downwash x = x coordinate, origin at leading-edge root, positive aft y = y coordinate, origin at leading-edge root, positive spanwise Z = vertical deformation of surface Z () j = complex amplitude of yth mode Presented as Paper 93-1364 at the AIAA 34th Structures, Struc-z = z coordinate, origin at leading-edge root, positive up a = angle of attack p = density a = real part of eigenvalue \\textless/\\textgreaterj = yth mode shape function \\textlessl\\textgreaterj = yth integrated mode shape function for calculating harmonic pressures (0-circular frequency Subscripts le = value of quantity at leading edge of wing or vehicle lower = value of quantity on lower surface of wing or vehicle ss = steady state or static aeroelastic value of quantity te = value of quantity at trailing edge of wing or vehicle upper = value of quantity on upper surface of wing or vehicle 3° = freestream value of quantity Superscripts I = harmonic part of quantity R = static part of quantity\n
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\n \n\n \n \n Jacobson, P L; Labelle, R D; Sturrus, W G; Ward, R F; and Lundeen, S R\n\n\n \n \n \n \n \n Optical spectroscopy of high-L n=10 Rydberg states of nitrogen.\n \n \n \n \n\n\n \n\n\n\n Phys. Rev. A, 54(1): 314–322. July 1996.\n Publisher: American Physical Society\n\n\n\n
\n\n\n\n \n \n \"OpticalPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@article{jacobson1996,\n\ttitle = {Optical spectroscopy of high-{L} n=10 {Rydberg} states of nitrogen},\n\tvolume = {54},\n\turl = {https://link.aps.org/doi/10.1103/PhysRevA.54.314},\n\tdoi = {10.1103/PhysRevA.54.314},\n\tnumber = {1},\n\tjournal = {Phys. Rev. A},\n\tauthor = {Jacobson, P L and Labelle, R D and Sturrus, W G and Ward, R F and Lundeen, S R},\n\tmonth = jul,\n\tyear = {1996},\n\tnote = {Publisher: American Physical Society},\n\tpages = {314--322},\n}\n\n\n\n
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\n \n\n \n \n Nasuti, F.; Barbato, M.; and Bruno, C.\n\n\n \n \n \n \n Material-dependent catalytic recombination modeling for hypersonic flows.\n \n \n \n\n\n \n\n\n\n Journal of Thermophysics and Heat Transfer, 10(1): 131–136. May 1996.\n Publisher: American Inst. Aeronautics and Astronautics Inc.\n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
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@article{nasuti1996,\n\ttitle = {Material-dependent catalytic recombination modeling for hypersonic flows},\n\tvolume = {10},\n\tdoi = {10.2514/3.763},\n\tabstract = {A new model to predict catalytic recombination rates of O and N atoms over silica re-entry thermal protection system is reported. The model follows the general approach of Halpern and Rosner, but adds estimates of some key physical mechanism parameters based on realistic surface potentials. This novel feature can therefore produce rate expressions for any surface for which structure is known. Testing the model for N over W, and N and O over SiO2 produces recombination probabilities in good agreement with published measurements at high surface temperature. In the case of N and O over SiO2, the model accounts for surface NO production due to O and N cross recombination. Copyright © 1993 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.},\n\tnumber = {1},\n\tjournal = {Journal of Thermophysics and Heat Transfer},\n\tauthor = {Nasuti, F. and Barbato, M. and Bruno, C.},\n\tmonth = may,\n\tyear = {1996},\n\tnote = {Publisher: American Inst. Aeronautics and Astronautics Inc.},\n\tkeywords = {Activation Energy, CFD, Heat Transfer, Heterogeneous Catalysis, High Temperature Reusable Surface Insulation, Hypersonic Flows, Kinetic Theory of Gases, Number of Particles, Surface Modeling, Thermal Protection System},\n\tpages = {131--136},\n}\n\n\n\n
\n
\n\n\n
\n A new model to predict catalytic recombination rates of O and N atoms over silica re-entry thermal protection system is reported. The model follows the general approach of Halpern and Rosner, but adds estimates of some key physical mechanism parameters based on realistic surface potentials. This novel feature can therefore produce rate expressions for any surface for which structure is known. Testing the model for N over W, and N and O over SiO2 produces recombination probabilities in good agreement with published measurements at high surface temperature. In the case of N and O over SiO2, the model accounts for surface NO production due to O and N cross recombination. Copyright © 1993 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.\n
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\n \n\n \n \n Kovalev, V. L.; Kolesnikov, A. F.; Krupnov, A. A.; and Yakushin, M. I.\n\n\n \n \n \n \n \n Analysis of phenomenological models describing the catalytic properties of high-temperature reusable coatings.\n \n \n \n \n\n\n \n\n\n\n Fluid Dynamics 1997 31:6, 31(6): 910–919. 1996.\n Publisher: Springer\n\n\n\n
\n\n\n\n \n \n \"AnalysisPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{kovalev1996,\n\ttitle = {Analysis of phenomenological models describing the catalytic properties of high-temperature reusable coatings},\n\tvolume = {31},\n\turl = {https://link.springer.com/article/10.1007/BF02030113},\n\tdoi = {10.1007/BF02030113},\n\tabstract = {The possibilities of using phenomenological models, constructed on the basis of the ideally-adsorbed Langmuir layer theory, to describe the catalytic properties of the heat shield coatings of reusable hypersonic vehicles are analyzed on the basis of a comparison of the calculated heat flows and the effective catalytic activity coefficients with full-scale and laboratory experimental data.},\n\tnumber = {6},\n\tjournal = {Fluid Dynamics 1997 31:6},\n\tauthor = {Kovalev, V. L. and Kolesnikov, A. F. and Krupnov, A. A. and Yakushin, M. I.},\n\tyear = {1996},\n\tnote = {Publisher: Springer},\n\tkeywords = {Classical Mechanics, Classical and Continuum Physics, Engineering Fluid Dynamics, Fluid, and Aerodynamics},\n\tpages = {910--919},\n}\n\n\n\n
\n
\n\n\n
\n The possibilities of using phenomenological models, constructed on the basis of the ideally-adsorbed Langmuir layer theory, to describe the catalytic properties of the heat shield coatings of reusable hypersonic vehicles are analyzed on the basis of a comparison of the calculated heat flows and the effective catalytic activity coefficients with full-scale and laboratory experimental data.\n
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\n  \n 1995\n \n \n (3)\n \n \n
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\n \n\n \n \n Inouye, Y.\n\n\n \n \n \n \n OREX Flight - Quick Report and Lessons Learned.\n \n \n \n\n\n \n\n\n\n In Proceedings of the 2nd European Symposium, 1995. \n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{inouye1995,\n\ttitle = {{OREX} {Flight} - {Quick} {Report} and {Lessons} {Learned}},\n\tbooktitle = {Proceedings of the 2nd {European} {Symposium}},\n\tauthor = {Inouye, Yasutoshi},\n\tyear = {1995},\n}\n\n\n\n\n\n\n\n\n\n\n\n
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\n \n\n \n \n Wolf, B,\n editor.\n \n\n\n \n \n \n \n Handbook of Ion Sources.\n \n \n \n\n\n \n\n\n\n CRC Press, 1995.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@book{wolf1995,\n\ttitle = {Handbook of {Ion} {Sources}},\n\tpublisher = {CRC Press},\n\teditor = {Wolf, B},\n\tyear = {1995},\n}\n\n\n\n
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\n \n\n \n \n Plimpton, S.\n\n\n \n \n \n \n Fast Parallel Algorithms for Short-Range Molecular Dynamics.\n \n \n \n\n\n \n\n\n\n Journal of Computational Physics, 117(1): 1–19. March 1995.\n Publisher: Academic Press\n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{plimpton1995,\n\ttitle = {Fast {Parallel} {Algorithms} for {Short}-{Range} {Molecular} {Dynamics}},\n\tvolume = {117},\n\tdoi = {10.1006/JCPH.1995.1039},\n\tabstract = {Three parallel algorithms for classical molecular dynamics are presented. The first assigns each processor a fixed subset of atoms; the second assigns each a fixed subset of inter-atomic forces to compute; the third assigns each a fixed spatial region. The algorithms are suitable for molecular dynamics models which can be difficult to parallelize efficiently - those with short-range forces where the neighbors of each atom change rapidly. They can be implemented on any distributed-memory parallel machine which allows for message-passing of data between independently executing processors. The algorithms are tested on a standard Lennard-Jones benchmark problem for system sizes ranging from 500 to 100,000,000 atoms on several parallel supercomputers - the nCUBE 2, Intel iPSC/860 and Paragon, and Cray T3D. Comparing the results to the fastest reported vectorized Cray Y-MP and C90 algorithm shows that the current generation of parallel machines is competitive with conventional vector supercomputers even for small problems. For large problems, the spatial algorithm achieves parallel efficiencies of 90\\% and a 1840-node Intel Paragon performs up to 165 faster than a single Cray C9O processor. Trade-offs between the three algorithms and guidelines for adapting them to more complex molecular dynamics simulations are also discussed. © 1995 Academic Press, Inc.},\n\tnumber = {1},\n\tjournal = {Journal of Computational Physics},\n\tauthor = {Plimpton, Steve},\n\tmonth = mar,\n\tyear = {1995},\n\tnote = {Publisher: Academic Press},\n\tpages = {1--19},\n}\n\n\n\n
\n
\n\n\n
\n Three parallel algorithms for classical molecular dynamics are presented. The first assigns each processor a fixed subset of atoms; the second assigns each a fixed subset of inter-atomic forces to compute; the third assigns each a fixed spatial region. The algorithms are suitable for molecular dynamics models which can be difficult to parallelize efficiently - those with short-range forces where the neighbors of each atom change rapidly. They can be implemented on any distributed-memory parallel machine which allows for message-passing of data between independently executing processors. The algorithms are tested on a standard Lennard-Jones benchmark problem for system sizes ranging from 500 to 100,000,000 atoms on several parallel supercomputers - the nCUBE 2, Intel iPSC/860 and Paragon, and Cray T3D. Comparing the results to the fastest reported vectorized Cray Y-MP and C90 algorithm shows that the current generation of parallel machines is competitive with conventional vector supercomputers even for small problems. For large problems, the spatial algorithm achieves parallel efficiencies of 90% and a 1840-node Intel Paragon performs up to 165 faster than a single Cray C9O processor. Trade-offs between the three algorithms and guidelines for adapting them to more complex molecular dynamics simulations are also discussed. © 1995 Academic Press, Inc.\n
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\n  \n 1994\n \n \n (5)\n \n \n
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\n \n\n \n \n Bertin, J. J.\n\n\n \n \n \n \n Hypersonic Aerothermodynamics.\n \n \n \n\n\n \n\n\n\n of AIAA education seriesAmerican Institute of Aeronautics and Astronautics, Washington, DC, 1994.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@book{bertin_hypersonic_1994,\n\taddress = {Washington, DC},\n\tseries = {{AIAA} education series},\n\ttitle = {Hypersonic {Aerothermodynamics}},\n\tisbn = {978-1-56347-036-3},\n\tpublisher = {American Institute of Aeronautics and Astronautics},\n\tauthor = {Bertin, John J.},\n\tyear = {1994},\n\tkeywords = {Aerothermodynamics, Design and construction Mathematical models, Hypersonic planes, Mathematics},\n}\n\n\n\n\n\n\n\n
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\n \n\n \n \n Menter, F. R.\n\n\n \n \n \n \n Two-Equation Eddy-Viscosity Turbulence Models for Engineering Applications.\n \n \n \n\n\n \n\n\n\n AIAA Journal, 32(8). August 1994.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{menter1994,\n\ttitle = {Two-{Equation} {Eddy}-{Viscosity} {Turbulence} {Models} for {Engineering} {Applications}},\n\tvolume = {32},\n\tdoi = {https://doi.org/10.2514/3.12149},\n\tnumber = {8},\n\tjournal = {AIAA Journal},\n\tauthor = {Menter, F. R.},\n\tmonth = aug,\n\tyear = {1994},\n}\n\n\n\n
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\n \n\n \n \n Netzer, D. W.\n\n\n \n \n \n \n Propulsion and Energetics Panel Working Group 22 on Experimental and Analytical Methods for the Determination of Connected-Pipe Ramjet and Ducted Rocket Internal Performance.\n \n \n \n\n\n \n\n\n\n Technical Report AGARD-AR-323, 1994.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@techreport{netzer1994,\n\ttitle = {Propulsion and {Energetics} {Panel} {Working} {Group} 22 on {Experimental} and {Analytical} {Methods} for the {Determination} of {Connected}-{Pipe} {Ramjet} and {Ducted} {Rocket} {Internal} {Performance}},\n\tnumber = {AGARD-AR-323},\n\tauthor = {Netzer, David W.},\n\tyear = {1994},\n}\n\n\n\n
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\n \n\n \n \n Maniatty, A. M.; and Zabaras, N. J.\n\n\n \n \n \n \n Investigation of regularization parameters and error estimating in inverse elasticity problems.\n \n \n \n\n\n \n\n\n\n International Journal for Numerical Methods in Engineering, 37(6): 1039–1052. March 1994.\n Publisher: John Wiley & Sons, Ltd\n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{maniatty1994,\n\ttitle = {Investigation of regularization parameters and error estimating in inverse elasticity problems},\n\tvolume = {37},\n\tdoi = {10.1002/NME.1620370610},\n\tabstract = {The method of Tarantola1 based on Bayesian statistical theory for solving general inverse problems is applied to inverse elasticity problems and is compared to the spatial regularization technique presented in Schnur and Zabaras.2 It is shown that when normal Gaussian distributions are assumed and the error in the data is uncorrelated, the Bayesian statistical theory takes a form similar to the deterministic regularization method presented earlier in Schnur and Zabaras,2 As such, the statistical theory can be used to provide a statistical interpretation of regularization and to estimate error in the solution of the inverse problem. Examples are presented to demonstrate the effect of the regularization parameters and the error in the initial data on the solution. Copyright © 1994 John Wiley \\& Sons, Ltd},\n\tnumber = {6},\n\tjournal = {International Journal for Numerical Methods in Engineering},\n\tauthor = {Maniatty, Antoinette M. and Zabaras, Nicholas J.},\n\tmonth = mar,\n\tyear = {1994},\n\tnote = {Publisher: John Wiley \\& Sons, Ltd},\n\tpages = {1039--1052},\n}\n\n\n\n
\n
\n\n\n
\n The method of Tarantola1 based on Bayesian statistical theory for solving general inverse problems is applied to inverse elasticity problems and is compared to the spatial regularization technique presented in Schnur and Zabaras.2 It is shown that when normal Gaussian distributions are assumed and the error in the data is uncorrelated, the Bayesian statistical theory takes a form similar to the deterministic regularization method presented earlier in Schnur and Zabaras,2 As such, the statistical theory can be used to provide a statistical interpretation of regularization and to estimate error in the solution of the inverse problem. Examples are presented to demonstrate the effect of the regularization parameters and the error in the initial data on the solution. Copyright © 1994 John Wiley & Sons, Ltd\n
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\n \n\n \n \n Gordon, S; and McBride, B J\n\n\n \n \n \n \n Computer Program for Calculation of Complex Chemical Equilibrium Compositions and Applications.\n \n \n \n\n\n \n\n\n\n Technical Report 1994.\n Issue: NASA-RP-1311\n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@techreport{gordon1994,\n\ttitle = {Computer {Program} for {Calculation} of {Complex} {Chemical} {Equilibrium} {Compositions} and {Applications}},\n\tauthor = {Gordon, S and McBride, B J},\n\tyear = {1994},\n\tnote = {Issue: NASA-RP-1311},\n}\n\n\n\n
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\n  \n 1993\n \n \n (9)\n \n \n
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\n \n\n \n \n Hicks, J.\n\n\n \n \n \n \n Flight Testing of Airbreathing Hypersonic Vehicles.\n \n \n \n\n\n \n\n\n\n Technical Report NASA Technical Memorandum 4524, Dryden Flight Research Facility, 1993.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@techreport{hicks_flight_1993,\n\taddress = {Dryden Flight Research Facility},\n\ttitle = {Flight {Testing} of {Airbreathing} {Hypersonic} {Vehicles}},\n\tnumber = {NASA Technical Memorandum 4524},\n\tauthor = {Hicks, John},\n\tyear = {1993},\n}\n\n\n\n
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\n \n\n \n \n Blevins, R. D.; Holehouse, I.; and Wentz, K. R.\n\n\n \n \n \n \n Thermoacoustic loads and fatigue of hypersonic vehicle skin panels.\n \n \n \n\n\n \n\n\n\n Journal of Aircraft, 30(6): 971–978. May 1993.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{blevins1993,\n\ttitle = {Thermoacoustic loads and fatigue of hypersonic vehicle skin panels},\n\tvolume = {30},\n\tdoi = {10.2514/3.46441},\n\tabstract = {A thermo-vibro-acoustic analysis of skin panels for airbreathing hypersonic vehicles is made for a generic trajectory and vehicle design. Aerothermal analysis shows that impingement of the bow shock wave on the vehicle produces fluctuating pressures, and local heat fluxes greatly exceed those due to the attached turbulent boundary. Thermal analysis of carbon-carbon skin panels shows that maximum temperatures will exceed 2700°F (1480°C) at the top of the ascent trajectory. Engine acoustic analysis indicates that sound levels will exceed 170 dB. As a result, loads due to engine acoustics and shock impingement dominate the design of many transatmospheric vehicle skin panels. © 1992 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.},\n\tnumber = {6},\n\tjournal = {Journal of Aircraft},\n\tauthor = {Blevins, Robert D. and Holehouse, Ian and Wentz, Kenneth R.},\n\tmonth = may,\n\tyear = {1993},\n\tkeywords = {Acoustic Vibrations, Airbreathing Hypersonic Vehicle, Blended Wing Body, Bow Shock, Finite Element Dynamic Analysis, Heat Flux, Hypersonic Vehicles, Laminar Turbulent Transition, Overall Sound Pressure Level, Transient Thermal Analysis},\n\tpages = {971--978},\n}\n\n\n\n
\n
\n\n\n
\n A thermo-vibro-acoustic analysis of skin panels for airbreathing hypersonic vehicles is made for a generic trajectory and vehicle design. Aerothermal analysis shows that impingement of the bow shock wave on the vehicle produces fluctuating pressures, and local heat fluxes greatly exceed those due to the attached turbulent boundary. Thermal analysis of carbon-carbon skin panels shows that maximum temperatures will exceed 2700°F (1480°C) at the top of the ascent trajectory. Engine acoustic analysis indicates that sound levels will exceed 170 dB. As a result, loads due to engine acoustics and shock impingement dominate the design of many transatmospheric vehicle skin panels. © 1992 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.\n
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\n \n\n \n \n Snel, H.; Houwink, R.; Bosschers, J.; Piers, W. J.; Van Bussel, G. J. W.; and Bruning, A.\n\n\n \n \n \n \n Sectional prediction of s-D effects for stalled flow on rotating blades and comparison with measurements.\n \n \n \n\n\n \n\n\n\n Technical Report 1993.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@techreport{snel1993,\n\ttitle = {Sectional prediction of s-{D} effects for stalled flow on rotating blades and comparison with measurements},\n\tauthor = {Snel, H. and Houwink, R. and Bosschers, J. and Piers, W. J. and Van Bussel, G. J. W. and Bruning, A.},\n\tyear = {1993},\n}\n\n\n\n
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\n \n\n \n \n Park, C.\n\n\n \n \n \n \n Review of Chemical-Kinetic Problems of Future NASA Missions, I: Earth Entries.\n \n \n \n\n\n \n\n\n\n Journal of Thermophysics and Heat Transfer, 7(2): 385–398. 1993.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{park1993,\n\ttitle = {Review of {Chemical}-{Kinetic} {Problems} of {Future} {NASA} {Missions}, {I}: {Earth} {Entries}},\n\tvolume = {7},\n\tdoi = {10.2514/3.431},\n\tnumber = {2},\n\tjournal = {Journal of Thermophysics and Heat Transfer},\n\tauthor = {Park, Chul},\n\tyear = {1993},\n\tpages = {385--398},\n}\n\n\n\n
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\n \n\n \n \n Smith, F.\n\n\n \n \n \n \n Atmospheric Propogation of Radiation.\n \n \n \n\n\n \n\n\n\n In The Infrared and Electro-Optical Systems Handbook, volume 2. SPIE Optical Engineering Press, 1993.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@incollection{smith1993,\n\ttitle = {Atmospheric {Propogation} of {Radiation}},\n\tvolume = {2},\n\tbooktitle = {The {Infrared} and {Electro}-{Optical} {Systems} {Handbook}},\n\tpublisher = {SPIE Optical Engineering Press},\n\tauthor = {Smith, Frederick},\n\tyear = {1993},\n}\n\n\n\n
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\n \n\n \n \n Holden, M. S; Craig, J.; and Ratliff, A.\n\n\n \n \n \n \n Aero-Optical Facility and Results.\n \n \n \n\n\n \n\n\n\n In 1993. \n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{holden1993,\n\ttitle = {Aero-{Optical} {Facility} and {Results}},\n\tauthor = {Holden, Michael S and Craig, J. and Ratliff, A.},\n\tyear = {1993},\n}\n\n\n\n
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\n \n\n \n \n Fehér, M; and Martin, P A\n\n\n \n \n \n \n Ab initio calculations of the properties of NO+ in its ground electronic state X 1$Σ$+.\n \n \n \n\n\n \n\n\n\n Chemical Physics Letters, 215(6): 565–570. 1993.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{feher1993,\n\ttitle = {Ab initio calculations of the properties of {NO}+ in its ground electronic state {X} 1\\$Σ\\$+},\n\tvolume = {215},\n\tdoi = {10.1016/0009-2614(93)89356-M},\n\tabstract = {The potential energy curves, dipole, quadrupole, octopole and hexadecapole moment functions of the ground X 1Σ+ state of NO+ have been calculated at Hartree-Fock, CASSCF, MR-CI and MP2 levels using a [8s6p3d] basis set. In addition, dipole polarisabilities have also been calculated at the HF and MP2 level. Results for the quadrupole moment and dipole polarisabilities compare favourably with recent experimental results from the spectroscopy of NO Rydberg states.},\n\tnumber = {6},\n\tjournal = {Chemical Physics Letters},\n\tauthor = {Fehér, M and Martin, P A},\n\tyear = {1993},\n\tpages = {565--570},\n}\n\n\n\n
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\n The potential energy curves, dipole, quadrupole, octopole and hexadecapole moment functions of the ground X 1Σ+ state of NO+ have been calculated at Hartree-Fock, CASSCF, MR-CI and MP2 levels using a [8s6p3d] basis set. In addition, dipole polarisabilities have also been calculated at the HF and MP2 level. Results for the quadrupole moment and dipole polarisabilities compare favourably with recent experimental results from the spectroscopy of NO Rydberg states.\n
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\n \n\n \n \n Fernandez, F A; Yong, Y C; and Ettinger, R D\n\n\n \n \n \n \n A simple adaptive mesh generator for 2-D finite element calculations (optical waveguide theory).\n \n \n \n\n\n \n\n\n\n IEEE Transactions on Magnetics, 29(2): 1882–1885. March 1993.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@article{fernandez1993,\n\ttitle = {A simple adaptive mesh generator for 2-{D} finite element calculations (optical waveguide theory)},\n\tvolume = {29},\n\tdoi = {10.1109/20.250774},\n\tnumber = {2},\n\tjournal = {IEEE Transactions on Magnetics},\n\tauthor = {Fernandez, F A and Yong, Y C and Ettinger, R D},\n\tmonth = mar,\n\tyear = {1993},\n\tpages = {1882--1885},\n}\n\n\n\n
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\n \n\n \n \n Liou, M. S.; and Steffen, C. J.\n\n\n \n \n \n \n A New Flux Splitting Scheme.\n \n \n \n\n\n \n\n\n\n Journal of Computational Physics, 107(1): 23–39. July 1993.\n Publisher: Academic Press\n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{liou1993,\n\ttitle = {A {New} {Flux} {Splitting} {Scheme}},\n\tvolume = {107},\n\tdoi = {10.1006/JCPH.1993.1122},\n\tabstract = {A new flux splitting scheme is proposed. The scheme is remarkably simple and yet its accuracy rivals, and in some cases surpasses, that of Roe's solver in the Euler and Navier-Stokes solutions carried out in this study, The scheme is robust and converges as fast as the Roe splitting. We propose an appropriately defined cell-face advection Mach number using values from the two straddling cells via associated characteristic speeds. This interface Mach number is then used to determine the upwind extrapolation for the convective quantities. Accordingly, the name of the scheme is coined as the advection upstream splitting method (AUSM). We also introduce a new pressure splitting which is shown to behave successfully, yielding much smoother results than other existing pressure splittings. Of particular interest is the supersonic blunt body problem in which the Roe scheme gives anomalous solutions. The AUSM produces correct solutions without difficulty for a wide range of flow conditions as well as grids. © 1993 Academic Press, Inc.},\n\tnumber = {1},\n\tjournal = {Journal of Computational Physics},\n\tauthor = {Liou, Meng Sing and Steffen, Christopher J.},\n\tmonth = jul,\n\tyear = {1993},\n\tnote = {Publisher: Academic Press},\n\tpages = {23--39},\n}\n\n\n\n
\n
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\n A new flux splitting scheme is proposed. The scheme is remarkably simple and yet its accuracy rivals, and in some cases surpasses, that of Roe's solver in the Euler and Navier-Stokes solutions carried out in this study, The scheme is robust and converges as fast as the Roe splitting. We propose an appropriately defined cell-face advection Mach number using values from the two straddling cells via associated characteristic speeds. This interface Mach number is then used to determine the upwind extrapolation for the convective quantities. Accordingly, the name of the scheme is coined as the advection upstream splitting method (AUSM). We also introduce a new pressure splitting which is shown to behave successfully, yielding much smoother results than other existing pressure splittings. Of particular interest is the supersonic blunt body problem in which the Roe scheme gives anomalous solutions. The AUSM produces correct solutions without difficulty for a wide range of flow conditions as well as grids. © 1993 Academic Press, Inc.\n
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\n  \n 1992\n \n \n (4)\n \n \n
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\n \n\n \n \n Spalart, P. R.; and Allmaras, S. R.\n\n\n \n \n \n \n A One-Equation Turbulence Model for Aerodynamic Flows.\n \n \n \n\n\n \n\n\n\n In 30th Aerospace Sciences Meeting and Exhibit, Reno, NV, January 1992. AIAA\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{spalart1992,\n\taddress = {Reno, NV},\n\ttitle = {A {One}-{Equation} {Turbulence} {Model} for {Aerodynamic} {Flows}},\n\tdoi = {https://doi.org/10.2514/6.1992-439},\n\tbooktitle = {30th {Aerospace} {Sciences} {Meeting} and {Exhibit}},\n\tpublisher = {AIAA},\n\tauthor = {Spalart, P. R. and Allmaras, S. R.},\n\tmonth = jan,\n\tyear = {1992},\n}\n\n\n\n
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\n \n\n \n \n Noda, T.; Araki, H.; Abe, F.; and Okada, M.\n\n\n \n \n \n \n Microstructure and mechanical properties of CVI carbon fiber/ SiC composites.\n \n \n \n\n\n \n\n\n\n Journal of Nuclear Materials, 191-194: 539–543. September 1992.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@article{noda_microstructure_1992,\n\tseries = {Fusion {Reactor} {Materials} {Part} {A}},\n\ttitle = {Microstructure and mechanical properties of {CVI} carbon fiber/ {SiC} composites},\n\tvolume = {191-194},\n\tissn = {0022-3115},\n\tdoi = {10.1016/S0022-3115(09)80103-7},\n\tabstract = {Microstructures and mechanical properties of carbon fiber/SiC composites prepared with chemical vapor infiltration (CVI) were examined to optimize the process conditions such as reactant and infiltration temperature. Ethyl-trichloro-silane (ETS) and methyl-trichloro-silane (MTS) were used as a source of SiC. CVI was conducted for 108 ks at maximum under a pressure of 13.3 kPa at 1273–1573 K. The composite with a density higher than 80\\% was obtained at 1373–1423 K and 1423–1374 K from ETS and MTS, respectively. The main matrix formed was β SiC for both reactants. However, silicon also deposited in SiC matrix for MTS. Preferential wettability of SiC to the carbon fiber was observed, and graphite was detected in the interface between the matrix and the carbon fiber by TEM. Mechanical properties were evaluated by bend tests at room temperature. High strength of around 800 MPa was obtained for the composites if the thickness of the surface coated layer was less than 50 μm. Apparent fracture toughness of the present carbon fiber/SiC composite was 6–10 MPa m1/2 at room temperature.},\n\turldate = {2023-10-30},\n\tjournal = {Journal of Nuclear Materials},\n\tauthor = {Noda, T. and Araki, H. and Abe, F. and Okada, M.},\n\tmonth = sep,\n\tyear = {1992},\n\tpages = {539--543},\n}\n\n\n\n
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\n Microstructures and mechanical properties of carbon fiber/SiC composites prepared with chemical vapor infiltration (CVI) were examined to optimize the process conditions such as reactant and infiltration temperature. Ethyl-trichloro-silane (ETS) and methyl-trichloro-silane (MTS) were used as a source of SiC. CVI was conducted for 108 ks at maximum under a pressure of 13.3 kPa at 1273–1573 K. The composite with a density higher than 80% was obtained at 1373–1423 K and 1423–1374 K from ETS and MTS, respectively. The main matrix formed was β SiC for both reactants. However, silicon also deposited in SiC matrix for MTS. Preferential wettability of SiC to the carbon fiber was observed, and graphite was detected in the interface between the matrix and the carbon fiber by TEM. Mechanical properties were evaluated by bend tests at room temperature. High strength of around 800 MPa was obtained for the composites if the thickness of the surface coated layer was less than 50 μm. Apparent fracture toughness of the present carbon fiber/SiC composite was 6–10 MPa m1/2 at room temperature.\n
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\n \n\n \n \n Scott, C D\n\n\n \n \n \n \n Advances in Hypersonics: Modeling Hypersonic Flows.\n \n \n \n\n\n \n\n\n\n In volume 2, pages 175–250. Birkhauser, 1992.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@incollection{scott1992,\n\ttitle = {Advances in {Hypersonics}: {Modeling} {Hypersonic} {Flows}},\n\tvolume = {2},\n\tpublisher = {Birkhauser},\n\tauthor = {Scott, C D},\n\tyear = {1992},\n\tpages = {175--250},\n}\n\n\n\n
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\n \n\n \n \n Holden, M. S.\n\n\n \n \n \n \n A Preliminary Study Associated with the Experimental Measurement of the Aero-Optic Characteristics of Hypersonic Configurations.\n \n \n \n\n\n \n\n\n\n Technical Report 1992.\n \n\n\n\n
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@techreport{holden1992,\n\ttitle = {A {Preliminary} {Study} {Associated} with the {Experimental} {Measurement} of the {Aero}-{Optic} {Characteristics} of {Hypersonic} {Configurations}},\n\tauthor = {Holden, M. S.},\n\tyear = {1992},\n}\n\n\n\n
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\n  \n 1991\n \n \n (6)\n \n \n
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\n \n\n \n \n Sharma, S P; Gillespie, W D; and Meyer, S A\n\n\n \n \n \n \n Shock Front Radiation Measurements in Air.\n \n \n \n\n\n \n\n\n\n In January 1991. \\AIAA Paper\\ 91-0573\n \n\n\n\n
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@inproceedings{sharma1991,\n\ttitle = {Shock {Front} {Radiation} {Measurements} in {Air}},\n\tpublisher = {\\{AIAA Paper\\} 91-0573},\n\tauthor = {Sharma, S P and Gillespie, W D and Meyer, S A},\n\tmonth = jan,\n\tyear = {1991},\n}\n\n\n\n
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\n \n\n \n \n Varandas, A J C; and Pais, A A C C\n\n\n \n \n \n \n Double Many-Body Expansion Potential Energy Surface for O4(3A), Dynamics of the O(3P) + O3(1A1) Reaction, and Second Virial Coefficients of Molecular Oxygen.\n \n \n \n\n\n \n\n\n\n In pages 55–78. Springer Netherlands, Dordrecht, 1991.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@incollection{varandas1991,\n\taddress = {Dordrecht},\n\ttitle = {Double {Many}-{Body} {Expansion} {Potential} {Energy} {Surface} for {O4}({3A}), {Dynamics} of the {O}({3P}) + {O3}({1A1}) {Reaction}, and {Second} {Virial} {Coefficients} of {Molecular} {Oxygen}},\n\tisbn = {978-94-011-3584-9},\n\tpublisher = {Springer Netherlands},\n\tauthor = {Varandas, A J C and Pais, A A C C},\n\tyear = {1991},\n\tdoi = {10.1007/978-94-011-3584-9_4},\n\tpages = {55--78},\n}\n\n\n\n
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\n \n\n \n \n Candler, G. V; and MacCormack, R. W\n\n\n \n \n \n \n Computation of Weakly Ionized Hypersonic Flows in Thermochemical Nonequilibrium.\n \n \n \n\n\n \n\n\n\n Journal of Thermophysics and Heat Transfer, 5(3): 266–273. 1991.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@article{candler1991,\n\ttitle = {Computation of {Weakly} {Ionized} {Hypersonic} {Flows} in {Thermochemical} {Nonequilibrium}},\n\tvolume = {5},\n\tnumber = {3},\n\tjournal = {Journal of Thermophysics and Heat Transfer},\n\tauthor = {Candler, Graham V and MacCormack, Robert W},\n\tyear = {1991},\n\tpages = {266--273},\n}\n\n\n\n
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\n \n\n \n \n Sheridan, T E; and Goree, J\n\n\n \n \n \n \n Collisional plasma sheath model.\n \n \n \n\n\n \n\n\n\n Physics of Fluids B: Plasma Physics, 3: 2796–2804. 1991.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@article{sheridan1991,\n\ttitle = {Collisional plasma sheath model},\n\tvolume = {3},\n\tjournal = {Physics of Fluids B: Plasma Physics},\n\tauthor = {Sheridan, T E and Goree, J},\n\tyear = {1991},\n\tpages = {2796--2804},\n}\n\n\n\n
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\n \n\n \n \n Page, J. A.; and Plotkin, K. J.\n\n\n \n \n \n \n An Efficient Method for Incorporating Computational Fluid Dynamics Into Sonic Boom Prediction.\n \n \n \n\n\n \n\n\n\n In pages 1–16, Baltimore, MD, 1991. \\AIAA Paper\\ 91-3275\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{page1991,\n\taddress = {Baltimore, MD},\n\ttitle = {An {Efficient} {Method} for {Incorporating} {Computational} {Fluid} {Dynamics} {Into} {Sonic} {Boom} {Prediction}},\n\tdoi = {10.2514/6.1991-3275},\n\tabstract = {A method has been developed for utilizing Computational Fluid Dynamics (CFD) flow solutions as a starting point for sonic boom propagation calculations. An existing CFD code was shown to predict near-field flew with adequate resolution for sonic boom analysis. However, within the flowfield domain for which this CFD calculation is practical, there can be significant unresolved diffraction effects. Neglecting these effects can underpredict boom at the ground. A matching methodology has therefore been developed, based on an acoustic multipole formulation. The multipole formulation allows a transformation from near-field flow to the final far-field azimuthal pattern. An example of the application of this methodology to a wing-body configuration is presented.},\n\tpublisher = {\\{AIAA Paper\\} 91-3275},\n\tauthor = {Page, Juliet A. and Plotkin, Kenneth J.},\n\tyear = {1991},\n\tpages = {1--16},\n}\n\n\n\n
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\n A method has been developed for utilizing Computational Fluid Dynamics (CFD) flow solutions as a starting point for sonic boom propagation calculations. An existing CFD code was shown to predict near-field flew with adequate resolution for sonic boom analysis. However, within the flowfield domain for which this CFD calculation is practical, there can be significant unresolved diffraction effects. Neglecting these effects can underpredict boom at the ground. A matching methodology has therefore been developed, based on an acoustic multipole formulation. The multipole formulation allows a transformation from near-field flow to the final far-field azimuthal pattern. An example of the application of this methodology to a wing-body configuration is presented.\n
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\n \n\n \n \n McCormack, E F; Pratt, S T; Dehmer, J L; and Dehmer, P M\n\n\n \n \n \n \n Analysis of the 8f, 9f, and 10f, v=1 Rydberg states of $\\{{\\}mathrm\\{{N}\\}\\}_\\{2\\}$.\n \n \n \n\n\n \n\n\n\n Phys. Rev. A, 44(5): 3007–3015. 1991.\n Publisher: American Physical Society\n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{mccormack1991,\n\ttitle = {Analysis of the 8f, 9f, and 10f, v=1 {Rydberg} states of \\$\\{{\\textbackslash}mathrm\\{{N}\\}\\}\\_\\{2\\}\\$},\n\tvolume = {44},\n\tdoi = {10.1103/PhysRevA.44.3007},\n\tnumber = {5},\n\tjournal = {Phys. Rev. A},\n\tauthor = {McCormack, E F and Pratt, S T and Dehmer, J L and Dehmer, P M},\n\tyear = {1991},\n\tnote = {Publisher: American Physical Society},\n\tpages = {3007--3015},\n}\n\n\n\n
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\n  \n 1990\n \n \n (6)\n \n \n
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\n \n\n \n \n Bushnell, D.\n\n\n \n \n \n \n \n Notes on Initial Disturbance Fields for the Transition Problem.\n \n \n \n \n\n\n \n\n\n\n In pages 217–232, 1990. Springer, New York, NY\n \n\n\n\n
\n\n\n\n \n \n \"NotesPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@inproceedings{bushnell1990,\n\ttitle = {Notes on {Initial} {Disturbance} {Fields} for the {Transition} {Problem}},\n\turl = {https://link.springer.com/chapter/10.1007/978-1-4612-3430-2_28},\n\tdoi = {10.1007/978-1-4612-3430-2_28},\n\tabstract = {The transition process is a 6-stage affair which is initiated by the ambient disturbance environment. These initial disturbance fields, which can be either stream- or body-generated (or a combination thereof) are processed by the body inviscid and viscous flow fields. The resulting disturbances then constitute the initial and bounding values for the subsequent linear and nonlinear growth processes which result, ultimately, in final breakdown to turbulence, e.g., the location of transition per se. The existing state of the art in transition estimation, the \\$e{\\textasciicircum}N\\$ method (e.g., Reference 1), deals only with the amplification ratio as given by linear theory and hence can only estimate (generally to better than 0(20 percent) currently) transition location when the initial disturbance fields are the equivalent of a “dull hum,” i.e., 0(.05 percent), as they appear to be in quiet, low- disturbance wind tunnels and many atmospheric flight situations. Improved prediction accuracy and/or predictions for non-canonical disturbance fields requires solution of transition as an initial-boundary value problem (via numerical simulations) and specification, for instance in flight, of the amplitude, spectra, orientation, and mode of all initial disturbance fields as a function of latitude, longitude, altitude, and time along the flight path.},\n\tpublisher = {Springer, New York, NY},\n\tauthor = {Bushnell, Dennis},\n\tyear = {1990},\n\tpages = {217--232},\n}\n\n\n\n
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\n The transition process is a 6-stage affair which is initiated by the ambient disturbance environment. These initial disturbance fields, which can be either stream- or body-generated (or a combination thereof) are processed by the body inviscid and viscous flow fields. The resulting disturbances then constitute the initial and bounding values for the subsequent linear and nonlinear growth processes which result, ultimately, in final breakdown to turbulence, e.g., the location of transition per se. The existing state of the art in transition estimation, the $e{\\textasciicircum}N$ method (e.g., Reference 1), deals only with the amplification ratio as given by linear theory and hence can only estimate (generally to better than 0(20 percent) currently) transition location when the initial disturbance fields are the equivalent of a “dull hum,” i.e., 0(.05 percent), as they appear to be in quiet, low- disturbance wind tunnels and many atmospheric flight situations. Improved prediction accuracy and/or predictions for non-canonical disturbance fields requires solution of transition as an initial-boundary value problem (via numerical simulations) and specification, for instance in flight, of the amplitude, spectra, orientation, and mode of all initial disturbance fields as a function of latitude, longitude, altitude, and time along the flight path.\n
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\n \n\n \n \n Park, C\n\n\n \n \n \n \n Nonequilbrium Hypersonic Aerothermodynamics.\n \n \n \n\n\n \n\n\n\n Wiley, New York, 1990.\n \n\n\n\n
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@book{park1990,\n\taddress = {New York},\n\ttitle = {Nonequilbrium {Hypersonic} {Aerothermodynamics}},\n\tpublisher = {Wiley},\n\tauthor = {Park, C},\n\tyear = {1990},\n}\n\n\n\n
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\n \n\n \n \n Park, C\n\n\n \n \n \n \n Nonequilbrium Hypersonic Aerothermodynamics.\n \n \n \n\n\n \n\n\n\n Wiley, New York, 1990.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@book{park1990a,\n\taddress = {New York},\n\ttitle = {Nonequilbrium {Hypersonic} {Aerothermodynamics}},\n\tpublisher = {Wiley},\n\tauthor = {Park, C},\n\tyear = {1990},\n}\n\n\n\n
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\n \n\n \n \n Kerl, K.\n\n\n \n \n \n \n \n Interferometric measurements of the dipole polarizability α of molecules between 300K and 1100K I. Monochromatic measurements at λ = 632-99 nm for the noble gases and H2, N2, O2, and CH4.\n \n \n \n \n\n\n \n\n\n\n Molecular Physics, 69(5): 803–817. 1990.\n Publisher: Taylor & Francis Group\n\n\n\n
\n\n\n\n \n \n \"InterferometricPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@article{kerl1990,\n\ttitle = {Interferometric measurements of the dipole polarizability α of molecules between {300K} and {1100K} {I}. {Monochromatic} measurements at λ = 632-99 nm for the noble gases and {H2}, {N2}, {O2}, and {CH4}},\n\tvolume = {69},\n\turl = {https://www.tandfonline.com/action/journalInformation?journalCode=tmph20},\n\tdoi = {10.1080/00268979000100611},\n\tabstract = {The temperature dependence of the dipole polarizability α(λ, T) of free atoms and molecules is determined by precise measurements of the refractive index n of gases in the extended temperature range between 300K and HOOK for wavelength λ = 632-99 nm, using a specially constructed Michelson twin interferometer, α of the noble gases is observed to be independent of T. α. of the molecular gases H2, N2, O2, and CH4 increases with increasing temperature by an amount of approximately 1 per cent per 1000 K. These results are in excellent agreement with theoretical predictions. They will be compared to previously measured temperature dependent polarizabilities. © 1990 Taylor \\& Francis Ltd.},\n\tnumber = {5},\n\tjournal = {Molecular Physics},\n\tauthor = {Kerl, Klaus},\n\tyear = {1990},\n\tnote = {Publisher: Taylor \\& Francis Group},\n\tpages = {803--817},\n}\n\n\n\n
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\n The temperature dependence of the dipole polarizability α(λ, T) of free atoms and molecules is determined by precise measurements of the refractive index n of gases in the extended temperature range between 300K and HOOK for wavelength λ = 632-99 nm, using a specially constructed Michelson twin interferometer, α of the noble gases is observed to be independent of T. α. of the molecular gases H2, N2, O2, and CH4 increases with increasing temperature by an amount of approximately 1 per cent per 1000 K. These results are in excellent agreement with theoretical predictions. They will be compared to previously measured temperature dependent polarizabilities. © 1990 Taylor & Francis Ltd.\n
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\n \n\n \n \n Nusca, M. J.; Chakravarthyt, S. R.; and Goldberg, U. C.\n\n\n \n \n \n \n Computational fluid dynamics capability for the solid-fuel ramjet projectile.\n \n \n \n\n\n \n\n\n\n Journal of Propulsion, 6(3): 256–262. May 1990.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
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@article{nusca1990,\n\ttitle = {Computational fluid dynamics capability for the solid-fuel ramjet projectile},\n\tvolume = {6},\n\tdoi = {10.2514/3.25428},\n\tabstract = {A computational fluid dynamics solution of the Navier-Stokes equations has been applied to the internal and external flow of inert solid-fuel ramjet projectiles. Computational modeling reveals internal flowfield details not attainable by flight or wind-tunnel measurements, thus contributing to the current investigation into the flight performance of solid-fuel ramjet projectiles. The present code employs numerical algorithms termed total variational diminishing (TVD). Computational solutions indicate the importance of several special features of the code, including the zonal grid framework, the TVD scheme, and a recently developed backflow turbulence model. The solutions are compared with results of internal surface pressure measurements. As demonstrated by these comparisons, the use of a backflow turbulence model distinguishes between satisfactory and poor flowfield predictions. © 1988 American Institute of Aeronautics and Astronautics.},\n\tnumber = {3},\n\tjournal = {Journal of Propulsion},\n\tauthor = {Nusca, Michael J. and Chakravarthyt, Sukumar R. and Goldberg, Uriel C.},\n\tmonth = may,\n\tyear = {1990},\n\tkeywords = {Baldwin Lomax Model, Baldwin Lomax Turbulence Model, Flight Performance, Navier Stokes Equations, Numerical Algorithms, Projectiles, Ramjet, Solid Fuels, Two Dimensional Flow, Wind Tunnel Models},\n\tpages = {256--262},\n}\n\n\n\n
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\n A computational fluid dynamics solution of the Navier-Stokes equations has been applied to the internal and external flow of inert solid-fuel ramjet projectiles. Computational modeling reveals internal flowfield details not attainable by flight or wind-tunnel measurements, thus contributing to the current investigation into the flight performance of solid-fuel ramjet projectiles. The present code employs numerical algorithms termed total variational diminishing (TVD). Computational solutions indicate the importance of several special features of the code, including the zonal grid framework, the TVD scheme, and a recently developed backflow turbulence model. The solutions are compared with results of internal surface pressure measurements. As demonstrated by these comparisons, the use of a backflow turbulence model distinguishes between satisfactory and poor flowfield predictions. © 1988 American Institute of Aeronautics and Astronautics.\n
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\n \n\n \n \n Gupta, R. N; Yos, J. M; Thompson, R. A; and Lee, K.\n\n\n \n \n \n \n A review of reaction rates and thermodynamic and transport properties for an 11-species air model for chemical and thermal nonequilibrium calculations to 30000 K.\n \n \n \n\n\n \n\n\n\n Technical Report 1990.\n Issue: NASA-RP-1232\n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@techreport{gupta1990,\n\ttitle = {A review of reaction rates and thermodynamic and transport properties for an 11-species air model for chemical and thermal nonequilibrium calculations to 30000 {K}},\n\tauthor = {Gupta, Roop N and Yos, Jerrold M and Thompson, Richard A and Lee, Kam-Pui},\n\tyear = {1990},\n\tnote = {Issue: NASA-RP-1232},\n}\n\n\n\n
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\n  \n 1989\n \n \n (7)\n \n \n
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\n \n\n \n \n Zannetti, L\n\n\n \n \n \n \n Time-Dependent Method to Solve the Inverse Problem for Internal Flows.\n \n \n \n\n\n \n\n\n\n AIAA Journal, 18(7). 1989.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{zannetti1989,\n\ttitle = {Time-{Dependent} {Method} to {Solve} the {Inverse} {Problem} for {Internal} {Flows}},\n\tvolume = {18},\n\tdoi = {10.2514/3.50816},\n\tabstract = {The objective of this paper is a numerical method for designing ducts with arbitrary prescribed pressure distribution at the walls. The method applies to inviscid compressible subsonic or transonic, two-dimensional or axisymmetric flows, and it is based on the time-dependent technique. The walls where the pressure distribution is prescribed are considered as flexible and impermeable. Starting from some initial guessed configuration, the computation follows the transient which occurs while the flexible walls move and finally reach a steady shape. Several numerical examples are described and compared with the solution of the direct problem in the case rff two-dimensional and axisymmetric subsonic diffusers, transonic nozzles and elbows. Nomenclature a = speed of sound b y c = see Fig. 1 c v = constant volume specific heat / = length p = pressure q = velocity u, w,u,w = velocity components (see Fig. 2) t = time x,z = rectangular coordinates P = logarithm of pressure R = gas constant S = entropy T. = temperature X,Z,r = transformed coordinates 7 = specific heats ratio 8 = angle in the polar frame of reference {\\textless}£ = see Fig. 2 {\\textbackslash}l/ = stream function All quantities are normalized with respect to reference values: / ref ,/? ref , r ref , tf ref = V*r ref , t rcf = (l ref /q nf), S ref = c v .},\n\tnumber = {7},\n\tjournal = {AIAA Journal},\n\tauthor = {Zannetti, L},\n\tyear = {1989},\n}\n\n\n\n
\n
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\n The objective of this paper is a numerical method for designing ducts with arbitrary prescribed pressure distribution at the walls. The method applies to inviscid compressible subsonic or transonic, two-dimensional or axisymmetric flows, and it is based on the time-dependent technique. The walls where the pressure distribution is prescribed are considered as flexible and impermeable. Starting from some initial guessed configuration, the computation follows the transient which occurs while the flexible walls move and finally reach a steady shape. Several numerical examples are described and compared with the solution of the direct problem in the case rff two-dimensional and axisymmetric subsonic diffusers, transonic nozzles and elbows. Nomenclature a = speed of sound b y c = see Fig. 1 c v = constant volume specific heat / = length p = pressure q = velocity u, w,u,w = velocity components (see Fig. 2) t = time x,z = rectangular coordinates P = logarithm of pressure R = gas constant S = entropy T. = temperature X,Z,r = transformed coordinates 7 = specific heats ratio 8 = angle in the polar frame of reference \\textless£ = see Fig. 2 \\l/ = stream function All quantities are normalized with respect to reference values: / ref ,/? ref , r ref , tf ref = V*r ref , t rcf = (l ref /q nf), S ref = c v .\n
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\n \n\n \n \n Tavella, D.; and Roberts, L.\n\n\n \n \n \n \n \n Transpiration cooling in hypersonic flight.\n \n \n \n \n\n\n \n\n\n\n Technical Report 1989.\n \n\n\n\n
\n\n\n\n \n \n \"TranspirationPaper\n  \n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@techreport{tavella1989,\n\ttitle = {Transpiration cooling in hypersonic flight},\n\turl = {https://ntrs.nasa.gov/citations/19900010736},\n\tabstract = {A preliminary numerical study of transpiration cooling applied to a hypersonic configuration is presented. Air transpiration is applied to the NASA all-body configuration flying at an altitude of 30500 m with a Mach number of 10.3. It was found that the amount of heat disposal by convection is determined primarily by the local geometry of the aircraft for moderate rates of transpiration. This property implies that different areas of the aircraft where transpiration occurs interact weakly with each other. A methodology for quick assessments of the transpiration requirements for a given flight configuration is presented.},\n\tauthor = {Tavella, Domingo and Roberts, Leonard},\n\tyear = {1989},\n}\n\n\n\n
\n
\n\n\n
\n A preliminary numerical study of transpiration cooling applied to a hypersonic configuration is presented. Air transpiration is applied to the NASA all-body configuration flying at an altitude of 30500 m with a Mach number of 10.3. It was found that the amount of heat disposal by convection is determined primarily by the local geometry of the aircraft for moderate rates of transpiration. This property implies that different areas of the aircraft where transpiration occurs interact weakly with each other. A methodology for quick assessments of the transpiration requirements for a given flight configuration is presented.\n
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\n \n\n \n \n MacCormack, R. W; and Candler, G. V\n\n\n \n \n \n \n The solution of the Navier-Stokes equations using Gauss-Seidel line relaxation.\n \n \n \n\n\n \n\n\n\n Computers & Fluids, 17(1): 135–150. 1989.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{maccormack1989,\n\ttitle = {The solution of the {Navier}-{Stokes} equations using {Gauss}-{Seidel} line relaxation},\n\tvolume = {17},\n\tdoi = {10.1016/0045-7930(89)90012-1},\n\tabstract = {Gauss-Seidel line relaxation is used to solve an implicit flux split difference approximation to the Navier-Stokes equations. The flux split approximation is chosen to maximize the weight of the diagonal elements of the block matrix elements that need to be inverted iteratively by the Gauss-Seidel procedure. There are several flux split approximations that can be chosen. However, not all are suitable for viscous flows containing shear or boundary layers. The present paper will illustrate the adverse effects of flux splitting in viscous flow calculations and propose corrections. The numerical procedures will be applied to solve for subsonic laminar flow past a flat plate, turbulent flow past a cone at March 6, and chemical and thermal nonequilibrium flow past a sphere-cone body at March 18.},\n\tnumber = {1},\n\tjournal = {Computers \\& Fluids},\n\tauthor = {MacCormack, Robert W and Candler, Graham V},\n\tyear = {1989},\n\tpages = {135--150},\n}\n\n\n\n
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\n\n\n
\n Gauss-Seidel line relaxation is used to solve an implicit flux split difference approximation to the Navier-Stokes equations. The flux split approximation is chosen to maximize the weight of the diagonal elements of the block matrix elements that need to be inverted iteratively by the Gauss-Seidel procedure. There are several flux split approximations that can be chosen. However, not all are suitable for viscous flows containing shear or boundary layers. The present paper will illustrate the adverse effects of flux splitting in viscous flow calculations and propose corrections. The numerical procedures will be applied to solve for subsonic laminar flow past a flat plate, turbulent flow past a cone at March 6, and chemical and thermal nonequilibrium flow past a sphere-cone body at March 18.\n
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\n \n\n \n \n Filloy, E.; and Rojano, T.\n\n\n \n \n \n \n Solving Equations: The Transition from Arithmetic to Algebra.\n \n \n \n\n\n \n\n\n\n For the Learning of Mathematics, 9(2): 19–25. 1989.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{filloy1989,\n\ttitle = {Solving {Equations}: {The} {Transition} from {Arithmetic} to {Algebra}},\n\tvolume = {9},\n\tnumber = {2},\n\tjournal = {For the Learning of Mathematics},\n\tauthor = {Filloy, E. and Rojano, T.},\n\tyear = {1989},\n\tpages = {19--25},\n}\n\n\n\n
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\n \n\n \n \n Plotkin, K. J.\n\n\n \n \n \n \n Review of Sonic Boom Theory.\n \n \n \n\n\n \n\n\n\n In pages 1–37, San Antonio, TX, 1989. \\AIAA Paper\\ 1989-1105\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{plotkin1989,\n\taddress = {San Antonio, TX},\n\ttitle = {Review of {Sonic} {Boom} {Theory}},\n\tdoi = {10.2514/6.1989-1105},\n\tabstract = {A review is presented of sonic boom theory, covering three viewpoints: historical perspective, an exposition of established boom theory and special phenomena, and the theoretical needs of current sonic boom problems. The review is intended to serve as a tutorial for the nonspecialist as well as a review of the current state-of-the-art and open issues. The greatest interest in sonic boom was associated with SST projects of the 1960s, and much of sonic boom theory has been shaped by that influence. Major elements of sonic boom analysis have been well established into what may be called standard theory. Current sonic boom problems require elements beyond standard theory, including the influence of hypersonic speeds, better integration of sonic boom analysis into the aircraft design process, and a more complete understanding of focal zones.},\n\tpublisher = {\\{AIAA Paper\\} 1989-1105},\n\tauthor = {Plotkin, Kenneth J.},\n\tyear = {1989},\n\tpages = {1--37},\n}\n\n\n\n
\n
\n\n\n
\n A review is presented of sonic boom theory, covering three viewpoints: historical perspective, an exposition of established boom theory and special phenomena, and the theoretical needs of current sonic boom problems. The review is intended to serve as a tutorial for the nonspecialist as well as a review of the current state-of-the-art and open issues. The greatest interest in sonic boom was associated with SST projects of the 1960s, and much of sonic boom theory has been shaped by that influence. Major elements of sonic boom analysis have been well established into what may be called standard theory. Current sonic boom problems require elements beyond standard theory, including the influence of hypersonic speeds, better integration of sonic boom analysis into the aircraft design process, and a more complete understanding of focal zones.\n
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\n \n\n \n \n Trella, M.\n\n\n \n \n \n \n Introduction to the Hypersonic Phenomena of Hermes.\n \n \n \n\n\n \n\n\n\n In Bertin, J. J.; Glowinski, R.; and Periaux, J., editor(s), Hypersonics, Volume 1: Defining the Hypersonic Environment. Birkhauser, 1989.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@incollection{trella1989,\n\ttitle = {Introduction to the {Hypersonic} {Phenomena} of {Hermes}},\n\tbooktitle = {Hypersonics, {Volume} 1: {Defining} the {Hypersonic} {Environment}},\n\tpublisher = {Birkhauser},\n\tauthor = {Trella, Massimo},\n\teditor = {Bertin, John J. and Glowinski, R. and Periaux, J.},\n\tyear = {1989},\n}\n\n\n\n
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\n \n\n \n \n Gnoffo, P. A; Gupta, R N; and Shinn, J L\n\n\n \n \n \n \n Conservation equations and physical models for hypersonic air flows in thermal and chemical nonequilibrium.\n \n \n \n\n\n \n\n\n\n Technical Report Hampton, Virginia, 1989.\n Issue: NASA-TP-2867\n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@techreport{gnoffo1989,\n\taddress = {Hampton, Virginia},\n\ttitle = {Conservation equations and physical models for hypersonic air flows in thermal and chemical nonequilibrium},\n\tauthor = {Gnoffo, Peter A and Gupta, R N and Shinn, J L},\n\tyear = {1989},\n\tnote = {Issue: NASA-TP-2867},\n}\n\n\n\n
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\n  \n 1988\n \n \n (8)\n \n \n
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\n \n\n \n \n Park, C.\n\n\n \n \n \n \n Assessment of a two-temperature kinetic model for dissociating and weakly ionizing nitrogen.\n \n \n \n\n\n \n\n\n\n Journal of Thermophysics and Heat Transfer, 2(1). 1988.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{park1988,\n\ttitle = {Assessment of a two-temperature kinetic model for dissociating and weakly ionizing nitrogen},\n\tvolume = {2},\n\tdoi = {10.2514/3.55},\n\tnumber = {1},\n\tjournal = {Journal of Thermophysics and Heat Transfer},\n\tauthor = {Park, Chul},\n\tyear = {1988},\n}\n\n\n\n
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\n \n\n \n \n Holden, M.; Wieting, A.; Moselle, J.; Wietingi, A.; Moselle, R; and Glass, C\n\n\n \n \n \n \n Studies of Aerothermal Loads Generated in Regions of ShockIShock Interaction in Hypersonic Flow.\n \n \n \n\n\n \n\n\n\n In 1988. \n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{holden1988a,\n\ttitle = {Studies of {Aerothermal} {Loads} {Generated} in {Regions} of {ShockIShock} {Interaction} in {Hypersonic} {Flow}},\n\tdoi = {10.2514/6.1988-477},\n\tabstract = {A study is presented of t h e aerothermal characteristics of regions of two-dimensional shocklshock interaction generated by the incidence of single and multiple shocks onto t h e bow shock ahead of a spanwise cylinder. Detailed measurements of the distribution of heat transfer and pressure were made in t h e peak heating regions around the cylinder for a number of shocklshock interactions which induced the greatest "interference heating". The studies were conducted in t h e 48" and 96" Shock Tunnels a t Calspan a t Mach numbers from 8 t o 19 with a two-dimensional wedge shock generatorttraverse cylinder model. The severity of the heat transfer gradients generated in the interaction regions requires an insulated model surface to prevent distortion by lateral heat conduction. However, models with low surface conductivity also result in large surface temperature rises in these inieiactjng flows, thereby presenting problems with data analysis. For transitional flows, the measurements demonstrated a large increase in the aerothermal loads with increasing Mach numbers which cannot be predicted by simple phenomenological models. However, t h e flow configurations t h a t exhibit t h e largest heating loads also appear to be inherently unstable and, therefore, cannot be predicted in detail using simple flow models. Flows with transition in the shear layer or boundary layer (which occurs a t relatively low Reynolds numbers (lo4)) also cannot be accurately predicted. The studies with multiple incident shocks demonstrate t h a t t h e largest aerothermal Ioads are generated on t h e cylinder when the shacks coalesce before they a r e incident on the bow shock. While a number of interesting flow fields are generated when two shocks a r e separately incident on the cylinder shock, the peak heating loads remain less than if they coalesce ahead of the bow shock. The presence of transition in t h e flow makes it difficult to predict aerothermal loads generated by multiple shock/shock interactions.},\n\tauthor = {Holden, MS and Wieting, Ar and Moselle, JR and Wietingi, Ar and Moselle, R and Glass, C},\n\tyear = {1988},\n}\n\n\n\n\n\n\n\n
\n
\n\n\n
\n A study is presented of t h e aerothermal characteristics of regions of two-dimensional shocklshock interaction generated by the incidence of single and multiple shocks onto t h e bow shock ahead of a spanwise cylinder. Detailed measurements of the distribution of heat transfer and pressure were made in t h e peak heating regions around the cylinder for a number of shocklshock interactions which induced the greatest \"interference heating\". The studies were conducted in t h e 48\" and 96\" Shock Tunnels a t Calspan a t Mach numbers from 8 t o 19 with a two-dimensional wedge shock generatorttraverse cylinder model. The severity of the heat transfer gradients generated in the interaction regions requires an insulated model surface to prevent distortion by lateral heat conduction. However, models with low surface conductivity also result in large surface temperature rises in these inieiactjng flows, thereby presenting problems with data analysis. For transitional flows, the measurements demonstrated a large increase in the aerothermal loads with increasing Mach numbers which cannot be predicted by simple phenomenological models. However, t h e flow configurations t h a t exhibit t h e largest heating loads also appear to be inherently unstable and, therefore, cannot be predicted in detail using simple flow models. Flows with transition in the shear layer or boundary layer (which occurs a t relatively low Reynolds numbers (lo4)) also cannot be accurately predicted. The studies with multiple incident shocks demonstrate t h a t t h e largest aerothermal Ioads are generated on t h e cylinder when the shacks coalesce before they a r e incident on the bow shock. While a number of interesting flow fields are generated when two shocks a r e separately incident on the cylinder shock, the peak heating loads remain less than if they coalesce ahead of the bow shock. The presence of transition in t h e flow makes it difficult to predict aerothermal loads generated by multiple shock/shock interactions.\n
\n\n\n
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\n \n\n \n \n Holden, M.; Wieting, A.; Moselle, J.; Wietingi, A.; Moselle, R; and Glass, C\n\n\n \n \n \n \n Studies of Aerothermal Loads Generated in Regions of ShockIShock Interaction in Hypersonic Flow.\n \n \n \n\n\n \n\n\n\n In 1988. \n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{holden1988,\n\ttitle = {Studies of {Aerothermal} {Loads} {Generated} in {Regions} of {ShockIShock} {Interaction} in {Hypersonic} {Flow}},\n\tdoi = {10.2514/6.1988-477},\n\tabstract = {A study is presented of t h e aerothermal characteristics of regions of two-dimensional shocklshock interaction generated by the incidence of single and multiple shocks onto t h e bow shock ahead of a spanwise cylinder. Detailed measurements of the distribution of heat transfer and pressure were made in t h e peak heating regions around the cylinder for a number of shocklshock interactions which induced the greatest "interference heating". The studies were conducted in t h e 48" and 96" Shock Tunnels a t Calspan a t Mach numbers from 8 t o 19 with a two-dimensional wedge shock generatorttraverse cylinder model. The severity of the heat transfer gradients generated in the interaction regions requires an insulated model surface to prevent distortion by lateral heat conduction. However, models with low surface conductivity also result in large surface temperature rises in these inieiactjng flows, thereby presenting problems with data analysis. For transitional flows, the measurements demonstrated a large increase in the aerothermal loads with increasing Mach numbers which cannot be predicted by simple phenomenological models. However, t h e flow configurations t h a t exhibit t h e largest heating loads also appear to be inherently unstable and, therefore, cannot be predicted in detail using simple flow models. Flows with transition in the shear layer or boundary layer (which occurs a t relatively low Reynolds numbers (lo4)) also cannot be accurately predicted. The studies with multiple incident shocks demonstrate t h a t t h e largest aerothermal Ioads are generated on t h e cylinder when the shacks coalesce before they a r e incident on the bow shock. While a number of interesting flow fields are generated when two shocks a r e separately incident on the cylinder shock, the peak heating loads remain less than if they coalesce ahead of the bow shock. The presence of transition in t h e flow makes it difficult to predict aerothermal loads generated by multiple shock/shock interactions.},\n\tauthor = {Holden, MS and Wieting, Ar and Moselle, JR and Wietingi, Ar and Moselle, R and Glass, C},\n\tyear = {1988},\n}\n\n\n\n
\n
\n\n\n
\n A study is presented of t h e aerothermal characteristics of regions of two-dimensional shocklshock interaction generated by the incidence of single and multiple shocks onto t h e bow shock ahead of a spanwise cylinder. Detailed measurements of the distribution of heat transfer and pressure were made in t h e peak heating regions around the cylinder for a number of shocklshock interactions which induced the greatest \"interference heating\". The studies were conducted in t h e 48\" and 96\" Shock Tunnels a t Calspan a t Mach numbers from 8 t o 19 with a two-dimensional wedge shock generatorttraverse cylinder model. The severity of the heat transfer gradients generated in the interaction regions requires an insulated model surface to prevent distortion by lateral heat conduction. However, models with low surface conductivity also result in large surface temperature rises in these inieiactjng flows, thereby presenting problems with data analysis. For transitional flows, the measurements demonstrated a large increase in the aerothermal loads with increasing Mach numbers which cannot be predicted by simple phenomenological models. However, t h e flow configurations t h a t exhibit t h e largest heating loads also appear to be inherently unstable and, therefore, cannot be predicted in detail using simple flow models. Flows with transition in the shear layer or boundary layer (which occurs a t relatively low Reynolds numbers (lo4)) also cannot be accurately predicted. The studies with multiple incident shocks demonstrate t h a t t h e largest aerothermal Ioads are generated on t h e cylinder when the shacks coalesce before they a r e incident on the bow shock. While a number of interesting flow fields are generated when two shocks a r e separately incident on the cylinder shock, the peak heating loads remain less than if they coalesce ahead of the bow shock. The presence of transition in t h e flow makes it difficult to predict aerothermal loads generated by multiple shock/shock interactions.\n
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\n \n\n \n \n Candler, G. V\n\n\n \n \n \n \n The Computational of Weakly Ionized Flow in Nonequilibrium.\n \n \n \n\n\n \n\n\n\n . 1988.\n Place: Stanford, California\n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@article{candler1988,\n\ttitle = {The {Computational} of {Weakly} {Ionized} {Flow} in {Nonequilibrium}},\n\tauthor = {Candler, Graham V},\n\tyear = {1988},\n\tnote = {Place: Stanford, California},\n}\n\n\n\n
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\n \n\n \n \n East, R. A.; and Hutt, G. R.\n\n\n \n \n \n \n \n Comparison of predictions and experimental data for hypersonic pitching motion stability.\n \n \n \n \n\n\n \n\n\n\n Journal of Spacecraft and Rockets, 25(3): 225–233. May 1988.\n \n\n\n\n
\n\n\n\n \n \n \"ComparisonPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
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@article{east1988,\n\ttitle = {Comparison of predictions and experimental data for hypersonic pitching motion stability},\n\tvolume = {25},\n\turl = {https://arc.aiaa.org/doi/10.2514/3.25975},\n\tdoi = {10.2514/3.25975},\n\tabstract = {The stability of oscillatory motions of vehicles flying at hypersonic Mach numbers is of considerable relevance to their initial design. Methods are needed for quick and accurate predictions of stability and control that are applicable over a wide range of body shapes, angles of attack, and flow conditions without the need to resort to computationally time-consuming numerical flowfield calculation methods. The purpose of this paper is to present experimental and theoretical data concerning the static and dynamic pitching stability of pointed and blunted 10 deg semiangle cones and a double-flared hyperballistic shape. Although Newtonian theory gives inadequate accuracy of prediction, inviscid embedded Newtonian theory, which accounts for the reduced dynamic pressure and lower flow velocity in the embedded flow downstream of the strong bow shock, is shown to provide surprisingly good agreement with experimental data over a wide range of conditions. Comparisons with experimental results show that the broad flow features associated with nose bluntness, angle of attack, and center of gravity position and their effect on static and dynamic stability are well described in regimes not containing flow structural change. However, in some cases discrepancies exist between the predictions and experimental observations, and these have been attributed to a variety of viscous-flow phenomena involving boundary-layer transition and flow separation, including complex lee-surface vortical flows. © American Institute of Aeronautics and Astronautics, Inc., 1988, All rights reserved.},\n\tnumber = {3},\n\tjournal = {Journal of Spacecraft and Rockets},\n\tauthor = {East, R. A. and Hutt, G. R.},\n\tmonth = may,\n\tyear = {1988},\n\tkeywords = {Aerodynamic Characteristics, Aerodynamic Flows, Angle of Attack, Boundary Layer Transition, Hypersonic Flight, Hypersonic Vehicles, Pitch Stability, Pressure Coefficient, Shock Layers, Wind Tunnels},\n\tpages = {225--233},\n}\n\n\n\n
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\n\n\n
\n The stability of oscillatory motions of vehicles flying at hypersonic Mach numbers is of considerable relevance to their initial design. Methods are needed for quick and accurate predictions of stability and control that are applicable over a wide range of body shapes, angles of attack, and flow conditions without the need to resort to computationally time-consuming numerical flowfield calculation methods. The purpose of this paper is to present experimental and theoretical data concerning the static and dynamic pitching stability of pointed and blunted 10 deg semiangle cones and a double-flared hyperballistic shape. Although Newtonian theory gives inadequate accuracy of prediction, inviscid embedded Newtonian theory, which accounts for the reduced dynamic pressure and lower flow velocity in the embedded flow downstream of the strong bow shock, is shown to provide surprisingly good agreement with experimental data over a wide range of conditions. Comparisons with experimental results show that the broad flow features associated with nose bluntness, angle of attack, and center of gravity position and their effect on static and dynamic stability are well described in regimes not containing flow structural change. However, in some cases discrepancies exist between the predictions and experimental observations, and these have been attributed to a variety of viscous-flow phenomena involving boundary-layer transition and flow separation, including complex lee-surface vortical flows. © American Institute of Aeronautics and Astronautics, Inc., 1988, All rights reserved.\n
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\n \n\n \n \n Varandas, A J C; and Pais, A A C C\n\n\n \n \n \n \n A realistic double many-body expansion (\\DMBE\\) potential energy surface for ground-state \\O\\\\textsubscript\\3\\ from a multiproperty fit to ab initio calculations, and to experimental spectroscopic, inelastic scattering, and kinetic isotope thermal rate da.\n \n \n \n\n\n \n\n\n\n Molecular Physics, 65(4): 843–860. 1988.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@article{varandas1988b,\n\ttitle = {A realistic double many-body expansion (\\{{DMBE}\\}) potential energy surface for ground-state \\{{O}\\}{\\textbackslash}textsubscript\\{3\\} from a multiproperty fit to ab initio calculations, and to experimental spectroscopic, inelastic scattering, and kinetic isotope thermal rate da},\n\tvolume = {65},\n\tnumber = {4},\n\tjournal = {Molecular Physics},\n\tauthor = {Varandas, A J C and Pais, A A C C},\n\tyear = {1988},\n\tpages = {843--860},\n}\n\n\n\n
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\n \n\n \n \n Varandas, A J C; and Pais, A A C C\n\n\n \n \n \n \n A realistic double many-body expansion (\\DMBE\\) potential energy surface for ground-state \\O\\\\textsubscript\\3\\ from a multiproperty fit to ab initio calculations, and to experimental spectroscopic, inelastic scattering, and kinetic isotope thermal rate da.\n \n \n \n\n\n \n\n\n\n Molecular Physics, 65(4): 843–860. 1988.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{varandas1988a,\n\ttitle = {A realistic double many-body expansion (\\{{DMBE}\\}) potential energy surface for ground-state \\{{O}\\}{\\textbackslash}textsubscript\\{3\\} from a multiproperty fit to ab initio calculations, and to experimental spectroscopic, inelastic scattering, and kinetic isotope thermal rate da},\n\tvolume = {65},\n\tnumber = {4},\n\tjournal = {Molecular Physics},\n\tauthor = {Varandas, A J C and Pais, A A C C},\n\tyear = {1988},\n\tpages = {843--860},\n}\n\n\n\n
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\n \n\n \n \n Varandas, A J C; and Pais, A A C C\n\n\n \n \n \n \n A realistic double many-body expansion (\\DMBE\\) potential energy surface for ground-state \\O\\\\textsubscript\\3\\ from a multiproperty fit to ab initio calculations, and to experimental spectroscopic, inelastic scattering, and kinetic isotope thermal rate da.\n \n \n \n\n\n \n\n\n\n Molecular Physics, 65(4): 843–860. 1988.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@article{varandas1988,\n\ttitle = {A realistic double many-body expansion (\\{{DMBE}\\}) potential energy surface for ground-state \\{{O}\\}{\\textbackslash}textsubscript\\{3\\} from a multiproperty fit to ab initio calculations, and to experimental spectroscopic, inelastic scattering, and kinetic isotope thermal rate da},\n\tvolume = {65},\n\tnumber = {4},\n\tjournal = {Molecular Physics},\n\tauthor = {Varandas, A J C and Pais, A A C C},\n\tyear = {1988},\n\tpages = {843--860},\n}\n\n\n\n
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\n  \n 1987\n \n \n (1)\n \n \n
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\n \n\n \n \n Tarantola, A.\n\n\n \n \n \n \n Inverse Problem Theory: Methods for Data Fitting and Model Parameters Estimation.\n \n \n \n\n\n \n\n\n\n Elsevier, New York, 1987.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@book{tarantola1987,\n\taddress = {New York},\n\ttitle = {Inverse {Problem} {Theory}: {Methods} for {Data} {Fitting} and {Model} {Parameters} {Estimation}},\n\tpublisher = {Elsevier},\n\tauthor = {Tarantola, A.},\n\tyear = {1987},\n}\n\n\n\n
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\n  \n 1986\n \n \n (5)\n \n \n
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\n \n\n \n \n Roache, P. J.; Ghia, K. N.; and White, F. M.\n\n\n \n \n \n \n Editorial Policy Statement on the Control of Numerical Accuracy.\n \n \n \n\n\n \n\n\n\n Journal of Fluids Engineering, 108(1): 2. March 1986.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@article{roache1986,\n\ttitle = {Editorial {Policy} {Statement} on the {Control} of {Numerical} {Accuracy}},\n\tvolume = {108},\n\tissn = {0098-2202, 1528-901X},\n\tdoi = {10.1115/1.3242537},\n\tlanguage = {en},\n\tnumber = {1},\n\turldate = {2024-04-01},\n\tjournal = {Journal of Fluids Engineering},\n\tauthor = {Roache, Patrick J. and Ghia, Kirti N. and White, Frank M.},\n\tmonth = mar,\n\tyear = {1986},\n\tpages = {2},\n}\n\n\n\n\n\n\n\n
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\n \n\n \n \n Trimmer, L.; Cary; and Voisinet, R.\n\n\n \n \n \n \n The optimum hypersonic wind tunnel.\n \n \n \n\n\n \n\n\n\n In 14th Aerodynamic Testing Conference, West Palm Beach,FL,U.S.A., March 1986. American Institute of Aeronautics and Astronautics\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@inproceedings{trimmer_optimum_1986,\n\taddress = {West Palm Beach,FL,U.S.A.},\n\ttitle = {The optimum hypersonic wind tunnel},\n\tdoi = {10.2514/6.1986-739},\n\tlanguage = {en},\n\turldate = {2023-10-30},\n\tbooktitle = {14th  {Aerodynamic}  {Testing} {Conference}},\n\tpublisher = {American Institute of Aeronautics and Astronautics},\n\tauthor = {Trimmer, L. and Cary, Jr., A. and Voisinet, R.},\n\tmonth = mar,\n\tyear = {1986},\n}\n\n\n\n
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\n \n\n \n \n Tong, B. G.; and Hui, W. H.\n\n\n \n \n \n \n \n Unsteady embedded Newton-Busemann flow theory.\n \n \n \n \n\n\n \n\n\n\n Journal of Spacecraft and Rockets, 23(2): 129–135. May 1986.\n \n\n\n\n
\n\n\n\n \n \n \"UnsteadyPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
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@article{tong1986,\n\ttitle = {Unsteady embedded {Newton}-{Busemann} flow theory},\n\tvolume = {23},\n\turl = {https://arc.aiaa.org/doi/10.2514/3.25798},\n\tdoi = {10.2514/3.25798},\n\tabstract = {An unsteady, embedded Newton-Busemann flow theory is developed by extending the unsteady Newton- Busemann flow theory of Hui and Tobak to blunt bodies, incorporating the embedded Newtonian flow concept of Seiff and Ericsson. In this theory the unsteady surface pressure includes the Newtonian impact part plus Busemann’s centrifugal correction. Applications to dynamic stability of blunt bodies of revolution show that 1) the centrifugal pressure is just as important as the impact part and must not be neglected and 2) with its inclusion the complete theory is in good agreement with existing experiments for high Mach number flow. © American Institute of Aeronautics and Astronautics, Inc., 1986, All rights reserved.},\n\tnumber = {2},\n\tjournal = {Journal of Spacecraft and Rockets},\n\tauthor = {Tong, Bing Gang and Hui, W. H.},\n\tmonth = may,\n\tyear = {1986},\n\tkeywords = {Angle of Attack, Conservation of Mass, Flight Path Angle, Freestream Mach Number, Hypersonic Flight, Hypersonic Flows, Mass Flow Rate, Shock Layers, Specific Heat, Taylor Series},\n\tpages = {129--135},\n}\n\n\n\n
\n
\n\n\n
\n An unsteady, embedded Newton-Busemann flow theory is developed by extending the unsteady Newton- Busemann flow theory of Hui and Tobak to blunt bodies, incorporating the embedded Newtonian flow concept of Seiff and Ericsson. In this theory the unsteady surface pressure includes the Newtonian impact part plus Busemann’s centrifugal correction. Applications to dynamic stability of blunt bodies of revolution show that 1) the centrifugal pressure is just as important as the impact part and must not be neglected and 2) with its inclusion the complete theory is in good agreement with existing experiments for high Mach number flow. © American Institute of Aeronautics and Astronautics, Inc., 1986, All rights reserved.\n
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\n \n\n \n \n Hohm, U.; and Kerl, K.\n\n\n \n \n \n \n \n Temperature dependence of mean molecular polarizability of gas molecules.\n \n \n \n \n\n\n \n\n\n\n Molecular Physics, 58(3): 541–550. June 1986.\n Publisher: Taylor & Francis Group\n\n\n\n
\n\n\n\n \n \n \"TemperaturePaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{hohm1986,\n\ttitle = {Temperature dependence of mean molecular polarizability of gas molecules},\n\tvolume = {58},\n\turl = {https://www.tandfonline.com/action/journalInformation?journalCode=tmph20},\n\tdoi = {10.1080/00268978600101351},\n\tabstract = {The temperature dependence of the mean molecular polarizability of the gases He, Ar, H2, N2, O2 and C(CH3)4 has been investigated experimentally with precise interferometric measurements in the temperature range 208 K≤ T≤365 K. In all cases an increase of the polarizability with increasing temperature was observed. By use of the noble gases He and Ar as internal standards it is possible to derive a relation between our results and the simple theory of Bell [1]. © 1986 Taylor \\& Francis Group, LLC.},\n\tnumber = {3},\n\tjournal = {Molecular Physics},\n\tauthor = {Hohm, Uwe and Kerl, Klaus},\n\tmonth = jun,\n\tyear = {1986},\n\tnote = {Publisher: Taylor \\& Francis Group},\n\tpages = {541--550},\n}\n\n\n\n
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\n The temperature dependence of the mean molecular polarizability of the gases He, Ar, H2, N2, O2 and C(CH3)4 has been investigated experimentally with precise interferometric measurements in the temperature range 208 K≤ T≤365 K. In all cases an increase of the polarizability with increasing temperature was observed. By use of the noble gases He and Ar as internal standards it is possible to derive a relation between our results and the simple theory of Bell [1]. © 1986 Taylor & Francis Group, LLC.\n
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\n \n\n \n \n Bouanich, J.; and Blumenfeld, L\n\n\n \n \n \n \n On the vibration-rotational matrix elements for diatomic molecules.\n \n \n \n\n\n \n\n\n\n Journal of Quantitative Spectroscopy and Radiative Transfer, 36(2): 87–111. 1986.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{bouanich1986,\n\ttitle = {On the vibration-rotational matrix elements for diatomic molecules},\n\tvolume = {36},\n\tdoi = {10.1016/0022-4073(86)90114-7},\n\tabstract = {Theoretical expressions for the vibro-rotational matrix elements of powers of the reduced displacement from equilibrium, corresponding to the infrared and Raman transitions vJ→v′J′ with v′⩽v+4, are obtained in terms of quartic polynomials in m (or J), including contributions from theDunham potential-energy coefficients a1, a2, a3. It is shown that it is preferable to consider the coefficients of the vibration-rotation interaction function [Fv′v(m)]12 rather than the Herman-Wallis factors. Two formalisms derived from power series expansion of the vibration-rotational internuclear potential function have been applied to the infrared transitions v→v′ (with v = 0, 10, 20) of the ground electronic state of CO.},\n\tnumber = {2},\n\tjournal = {Journal of Quantitative Spectroscopy and Radiative Transfer},\n\tauthor = {Bouanich, J.-P. and Blumenfeld, L},\n\tyear = {1986},\n\tpages = {87--111},\n}\n\n\n\n
\n
\n\n\n
\n Theoretical expressions for the vibro-rotational matrix elements of powers of the reduced displacement from equilibrium, corresponding to the infrared and Raman transitions vJ→v′J′ with v′⩽v+4, are obtained in terms of quartic polynomials in m (or J), including contributions from theDunham potential-energy coefficients a1, a2, a3. It is shown that it is preferable to consider the coefficients of the vibration-rotation interaction function [Fv′v(m)]12 rather than the Herman-Wallis factors. Two formalisms derived from power series expansion of the vibration-rotational internuclear potential function have been applied to the infrared transitions v→v′ (with v = 0, 10, 20) of the ground electronic state of CO.\n
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\n  \n 1984\n \n \n (1)\n \n \n
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\n \n\n \n \n Lee, J.\n\n\n \n \n \n \n Basic governing equations for the flight regimes of aeroassisted orbital transfer vehicles.\n \n \n \n\n\n \n\n\n\n In pages 1–18, Snowmass, CO, June 1984. \\AIAA Paper\\ 1984-1729\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@inproceedings{lee1984,\n\taddress = {Snowmass, CO},\n\ttitle = {Basic governing equations for the flight regimes of aeroassisted orbital transfer vehicles},\n\tpublisher = {\\{AIAA Paper\\} 1984-1729},\n\tauthor = {Lee, Jong-Hun},\n\tmonth = jun,\n\tyear = {1984},\n\tpages = {1--18},\n}\n\n\n\n
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\n  \n 1983\n \n \n (2)\n \n \n
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\n \n\n \n \n Van Hooydonk, G\n\n\n \n \n \n \n Higher order spectroscopic constants and ionic potentials in molecular spectroscopy.\n \n \n \n\n\n \n\n\n\n Journal of Molecular Structure: THEOCHEM, 105(1): 69–90. 1983.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{vanhooydonk1983,\n\ttitle = {Higher order spectroscopic constants and ionic potentials in molecular spectroscopy},\n\tvolume = {105},\n\tdoi = {10.1016/0166-1280(83)80034-7},\n\tabstract = {Ionic Kratzer-type potentials (such as the Varshni V-potential) are shown to be consistent with all observed lower- and higher-order spectroscopic constants αe, ωeχe, βe and γe for over thirty diatomics of widely differing ionic characters. All higher Dunham coefficients can be derived from the first, which is itself related to the force constant. The ionic potentials are compared with other potentials discussed in the literature (Dunham, Morse, Simons---Parr−Finlan, Jordan). The deviations of Morse curves near re from RKR-curves are completely predictable using an ionic potential as reference. The Calder-Ruedenberg constant, applicable to 160 diatomics, is consistently accounted for. Calculated vibrational levels for Li2 on both sides of the minimum correspond with experimental levels within 0.6\\%, whereas computed ΔG(υ)-values are accurate to within 1\\%. For the excited state, A 1Σu+ of Li2 the same potential is also satisfactory. An ionic potential corrected for an atomic dissociation limit at r = ∞ produces a finite solution at r ≈ 0. In the case of Li2 the energy at r ≈ 10−4 Åis of the same order of magnitude as the experimental fusion energy of two Li-nuclei into a single C-nucleus.},\n\tnumber = {1},\n\tjournal = {Journal of Molecular Structure: THEOCHEM},\n\tauthor = {Van Hooydonk, G},\n\tyear = {1983},\n\tpages = {69--90},\n}\n\n\n\n
\n
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\n Ionic Kratzer-type potentials (such as the Varshni V-potential) are shown to be consistent with all observed lower- and higher-order spectroscopic constants αe, ωeχe, βe and γe for over thirty diatomics of widely differing ionic characters. All higher Dunham coefficients can be derived from the first, which is itself related to the force constant. The ionic potentials are compared with other potentials discussed in the literature (Dunham, Morse, Simons—Parr−Finlan, Jordan). The deviations of Morse curves near re from RKR-curves are completely predictable using an ionic potential as reference. The Calder-Ruedenberg constant, applicable to 160 diatomics, is consistently accounted for. Calculated vibrational levels for Li2 on both sides of the minimum correspond with experimental levels within 0.6%, whereas computed ΔG(υ)-values are accurate to within 1%. For the excited state, A 1Σu+ of Li2 the same potential is also satisfactory. An ionic potential corrected for an atomic dissociation limit at r = ∞ produces a finite solution at r ≈ 0. In the case of Li2 the energy at r ≈ 10−4 Åis of the same order of magnitude as the experimental fusion energy of two Li-nuclei into a single C-nucleus.\n
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\n \n\n \n \n Dmitrieva, I K; and Zenevich, V A\n\n\n \n \n \n \n A Simple Analytical Approximation for the Potential Energy of Diatomics.\n \n \n \n\n\n \n\n\n\n Chemical Physics Letters, 96(2): 228–231. 1983.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{dmitrieva1983,\n\ttitle = {A {Simple} {Analytical} {Approximation} for the {Potential} {Energy} of {Diatomics}},\n\tvolume = {96},\n\tdoi = {10.1016/0009-2614(83)80496-5},\n\tnumber = {2},\n\tjournal = {Chemical Physics Letters},\n\tauthor = {Dmitrieva, I K and Zenevich, V A},\n\tyear = {1983},\n\tpages = {228--231},\n}\n\n\n\n
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\n  \n 1981\n \n \n (2)\n \n \n
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\n \n\n \n \n Steger, J. L.; and Warming, R. F.\n\n\n \n \n \n \n Flux vector splitting of the inviscid gasdynamic equations with application to finite-difference methods.\n \n \n \n\n\n \n\n\n\n Journal of Computational Physics, 40(2): 263–293. April 1981.\n Publisher: Academic Press\n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{steger1981,\n\ttitle = {Flux vector splitting of the inviscid gasdynamic equations with application to finite-difference methods},\n\tvolume = {40},\n\tdoi = {10.1016/0021-9991(81)90210-2},\n\tabstract = {The conservation-law form of the inviscid gasdynamic equations has the remarkable property that the nonlinear flux vectors are homogeneous functions of degree one. This property readily permits the splitting of flux vectors into subvectors by similarity transformations so that each subvector has associated with it a specified eigenvalue spectrum. As a consequence of flux vector splitting, new explicit and implicit dissipative finite-difference schemes are developed for first-order hyperbolic systems of equations. Appropriate one-sided spatial differences for each split flux vector are used throughout the computational field even if the flow is locally subsonic. The results of some preliminary numerical computations are included. © 1981.},\n\tnumber = {2},\n\tjournal = {Journal of Computational Physics},\n\tauthor = {Steger, Joseph L. and Warming, R. F.},\n\tmonth = apr,\n\tyear = {1981},\n\tnote = {Publisher: Academic Press},\n\tpages = {263--293},\n}\n\n\n\n
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\n The conservation-law form of the inviscid gasdynamic equations has the remarkable property that the nonlinear flux vectors are homogeneous functions of degree one. This property readily permits the splitting of flux vectors into subvectors by similarity transformations so that each subvector has associated with it a specified eigenvalue spectrum. As a consequence of flux vector splitting, new explicit and implicit dissipative finite-difference schemes are developed for first-order hyperbolic systems of equations. Appropriate one-sided spatial differences for each split flux vector are used throughout the computational field even if the flow is locally subsonic. The results of some preliminary numerical computations are included. © 1981.\n
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\n \n\n \n \n Roe, P. L.\n\n\n \n \n \n \n Approximate Riemann solvers, parameter vectors, and difference schemes.\n \n \n \n\n\n \n\n\n\n Journal of Computational Physics, 43(2): 357–372. October 1981.\n Publisher: Academic Press\n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{roe1981,\n\ttitle = {Approximate {Riemann} solvers, parameter vectors, and difference schemes},\n\tvolume = {43},\n\tdoi = {10.1016/0021-9991(81)90128-5},\n\tabstract = {Several numerical schemes for the solution of hyperbolic conservation laws are based on exploiting the information obtained by considering a sequence of Riemann problems. It is argued that in existing schemes much of this information is degraded, and that only certain features of the exact solution are worth striving for. It is shown that these features can be obtained by constructing a matrix with a certain "Property U." Matrices having this property are exhibited for the equations of steady and unsteady gasdynamics. In order to construct thems it is found helpful to introduce "parameter vectors" which notably simplify the structure of the conservation laws. © 1981.},\n\tnumber = {2},\n\tjournal = {Journal of Computational Physics},\n\tauthor = {Roe, P. L.},\n\tmonth = oct,\n\tyear = {1981},\n\tnote = {Publisher: Academic Press},\n\tpages = {357--372},\n}\n\n\n\n
\n
\n\n\n
\n Several numerical schemes for the solution of hyperbolic conservation laws are based on exploiting the information obtained by considering a sequence of Riemann problems. It is argued that in existing schemes much of this information is degraded, and that only certain features of the exact solution are worth striving for. It is shown that these features can be obtained by constructing a matrix with a certain \"Property U.\" Matrices having this property are exhibited for the equations of steady and unsteady gasdynamics. In order to construct thems it is found helpful to introduce \"parameter vectors\" which notably simplify the structure of the conservation laws. © 1981.\n
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\n  \n 1980\n \n \n (1)\n \n \n
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\n \n\n \n \n Bird, G. A.\n\n\n \n \n \n \n \n Monte-Carlo simulation in an engineering context.\n \n \n \n \n\n\n \n\n\n\n In 1980. \n \n\n\n\n
\n\n\n\n \n \n \"Monte-CarloPaper\n  \n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{bird1980,\n\ttitle = {Monte-{Carlo} simulation in an engineering context},\n\turl = {https://ui.adsabs.harvard.edu/abs/1981PrAA...74..239B/abstract},\n\tauthor = {Bird, G. A.},\n\tyear = {1980},\n}\n\n\n\n
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\n  \n 1979\n \n \n (1)\n \n \n
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\n \n\n \n \n van Leer, B.\n\n\n \n \n \n \n Towards the ultimate conservative difference scheme. V. A second-order sequel to Godunov's method.\n \n \n \n\n\n \n\n\n\n Journal of Computational Physics, 32(1): 101–136. July 1979.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{vanleer1979,\n\ttitle = {Towards the ultimate conservative difference scheme. {V}. {A} second-order sequel to {Godunov}'s method},\n\tvolume = {32},\n\tissn = {0021-9991},\n\tdoi = {10.1016/0021-9991(79)90145-1},\n\tabstract = {A method of second-order accuracy is described for integrating the equations of ideal compressible flow. The method is based on the integral conservation laws and is dissipative, so that it can be used across shocks. The heart of the method is a one-dimensional Lagrangean scheme that may be regarded as a second-order sequel to Godunov's method. The second-order accuracy is achieved by taking the distributions of the state quantities inside a gas slab to be linear, rather than uniform as in Godunov's method. The Lagrangean results are remapped with least-squares accuracy onto the desired Euler grid in a separate step. Several monotonicity algorithms are applied to ensure positivity, monotonicity and nonlinear stability. Higher dimensions are covered through time splitting. Numerical results for one-dimensional and two-dimensional flows are presented, demonstrating the efficiency of the method. The paper concludes with a summary of the results of the whole series “Towards the Ultimate Conservative Difference Scheme.”},\n\tnumber = {1},\n\turldate = {2024-04-25},\n\tjournal = {Journal of Computational Physics},\n\tauthor = {van Leer, Bram},\n\tmonth = jul,\n\tyear = {1979},\n\tpages = {101--136},\n}\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n
\n
\n\n\n
\n A method of second-order accuracy is described for integrating the equations of ideal compressible flow. The method is based on the integral conservation laws and is dissipative, so that it can be used across shocks. The heart of the method is a one-dimensional Lagrangean scheme that may be regarded as a second-order sequel to Godunov's method. The second-order accuracy is achieved by taking the distributions of the state quantities inside a gas slab to be linear, rather than uniform as in Godunov's method. The Lagrangean results are remapped with least-squares accuracy onto the desired Euler grid in a separate step. Several monotonicity algorithms are applied to ensure positivity, monotonicity and nonlinear stability. Higher dimensions are covered through time splitting. Numerical results for one-dimensional and two-dimensional flows are presented, demonstrating the efficiency of the method. The paper concludes with a summary of the results of the whole series “Towards the Ultimate Conservative Difference Scheme.”\n
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\n  \n 1978\n \n \n (4)\n \n \n
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\n \n\n \n \n Wolfe, W L; and Zizzis, G J\n\n\n \n \n \n \n The Infrared Handbook.\n \n \n \n\n\n \n\n\n\n Technical Report 1978.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@techreport{wolfe1978,\n\ttitle = {The {Infrared} {Handbook}},\n\tauthor = {Wolfe, W L and Zizzis, G J},\n\tyear = {1978},\n}\n\n\n\n
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\n \n\n \n \n Bouanich, J B\n\n\n \n \n \n \n Matrix elements for the vibrational transitions 0 → 0 to 0 → 7 of diatomic molecules.\n \n \n \n\n\n \n\n\n\n Journal of Quantitative Spectroscopy and Radiative Transfer, 20(4): 419–423. 1978.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{bouanich1978,\n\ttitle = {Matrix elements for the vibrational transitions 0 → 0 to 0 → 7 of diatomic molecules},\n\tvolume = {20},\n\tdoi = {10.1016/0022-4073(78)90110-3},\n\tabstract = {The vibrational matrix elements, including sixth-order contributions, are given for the transitions 0 → υ′ (υ′ ⩽ 7), using an eighth-power internuclear Dunham potential and an eight-term power series expansion of the dipole moment.},\n\tnumber = {4},\n\tjournal = {Journal of Quantitative Spectroscopy and Radiative Transfer},\n\tauthor = {Bouanich, J B},\n\tyear = {1978},\n\tpages = {419--423},\n}\n\n\n\n
\n
\n\n\n
\n The vibrational matrix elements, including sixth-order contributions, are given for the transitions 0 → υ′ (υ′ ⩽ 7), using an eighth-power internuclear Dunham potential and an eight-term power series expansion of the dipole moment.\n
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\n\n\n
\n \n\n \n \n Halpern, B.; and Rosner, D. E.\n\n\n \n \n \n \n \n Chemical energy accommodation at catalyst surfaces. Flow reactor studies of the association of nitrogen atoms on metals at high temperatures.\n \n \n \n \n\n\n \n\n\n\n Journal of the Chemical Society, Faraday Transactions 1: Physical Chemistry in Condensed Phases, 74(0): 1883–1912. January 1978.\n Publisher: Royal Society of Chemistry\n\n\n\n
\n\n\n\n \n \n \"ChemicalPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{halpern1978,\n\ttitle = {Chemical energy accommodation at catalyst surfaces. {Flow} reactor studies of the association of nitrogen atoms on metals at high temperatures},\n\tvolume = {74},\n\turl = {https://pubs.rsc.org/en/content/articlelanding/1978/f1/f19787401883},\n\tdoi = {10.1039/F19787401883},\n\tabstract = {The fate of the energy release in highly exoergic surface-catalysed chemical reactions is of considerable fundamental interest and influences catalyst volatilization/sintering, the aerodynamic heating of hypersonic glide vehicles subject to bombardment by atomic nitrogen and atomic oxygen, etc. To provide the first available high temperature data (T {\\textgreater} 800 K) on what fraction (β) of the equilibrium (bond) dissociation energy is delivered to the catalyst per atom association event, a coaxial filament flow reactor (CFFR) has been developed, well-suited to both precise atom mass balance and isothermal calorimetric measurements. Experimental results for the chemical energy accommodation (CEA) coefficient β, and the corresponding N-atom recombination probabilities, γ, are presented for the metals Pt, Ir, Rh, Pd, Co, W and Re at temperatures up to 2600 K. Catalyst energy deposition can be an order of magnitude less than the equilibrium reaction energy. However, since this is not true at all surface temperatures, simple rankings of β-values for metals (at, say, room temperature) or correlations based only on one or two relevant system parameters (e.g. bulk Debye temperature) are of limited application. Alternatively, for N/Re, N/W a Langmuir-type mass-action analysis of the operative elementary steps, combined with a simple postulate (viz. Rideal-produced molecules leave excited whereas Langmuir - Hinshelwood (LH) produced molecules do not) provides a semi-quantitative understanding of β-trends in terms of the adatom binding energy, the equilibrium bond dissociation energy of the product molecule and an elementary Rideal reaction probability. However, high β-values can be observed at low temperatures if the system admits LH-reaction, or Rideal-formed excited molecules are rapidly quenched prior to desorption. We postulate that low catalyst energy deposition occurs at high temperatures (N/Pt, N/Ir) if LH-reaction occurs prior to the complete accommodation of the reactant (atom) chemisorption energy.},\n\tnumber = {0},\n\tjournal = {Journal of the Chemical Society, Faraday Transactions 1: Physical Chemistry in Condensed Phases},\n\tauthor = {Halpern, Bret and Rosner, Daniel E.},\n\tmonth = jan,\n\tyear = {1978},\n\tnote = {Publisher: Royal Society of Chemistry},\n\tpages = {1883--1912},\n}\n\n\n\n
\n
\n\n\n
\n The fate of the energy release in highly exoergic surface-catalysed chemical reactions is of considerable fundamental interest and influences catalyst volatilization/sintering, the aerodynamic heating of hypersonic glide vehicles subject to bombardment by atomic nitrogen and atomic oxygen, etc. To provide the first available high temperature data (T \\textgreater 800 K) on what fraction (β) of the equilibrium (bond) dissociation energy is delivered to the catalyst per atom association event, a coaxial filament flow reactor (CFFR) has been developed, well-suited to both precise atom mass balance and isothermal calorimetric measurements. Experimental results for the chemical energy accommodation (CEA) coefficient β, and the corresponding N-atom recombination probabilities, γ, are presented for the metals Pt, Ir, Rh, Pd, Co, W and Re at temperatures up to 2600 K. Catalyst energy deposition can be an order of magnitude less than the equilibrium reaction energy. However, since this is not true at all surface temperatures, simple rankings of β-values for metals (at, say, room temperature) or correlations based only on one or two relevant system parameters (e.g. bulk Debye temperature) are of limited application. Alternatively, for N/Re, N/W a Langmuir-type mass-action analysis of the operative elementary steps, combined with a simple postulate (viz. Rideal-produced molecules leave excited whereas Langmuir - Hinshelwood (LH) produced molecules do not) provides a semi-quantitative understanding of β-trends in terms of the adatom binding energy, the equilibrium bond dissociation energy of the product molecule and an elementary Rideal reaction probability. However, high β-values can be observed at low temperatures if the system admits LH-reaction, or Rideal-formed excited molecules are rapidly quenched prior to desorption. We postulate that low catalyst energy deposition occurs at high temperatures (N/Pt, N/Ir) if LH-reaction occurs prior to the complete accommodation of the reactant (atom) chemisorption energy.\n
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\n \n\n \n \n Kenworthy, M.\n\n\n \n \n \n \n A Study of Unstable Axisymmetric Seperation in High Speed Flows.\n \n \n \n\n\n \n\n\n\n . 1978.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{kenworthy1978,\n\ttitle = {A {Study} of {Unstable} {Axisymmetric} {Seperation} in {High} {Speed} {Flows}},\n\tauthor = {Kenworthy, M.},\n\tyear = {1978},\n}\n\n\n\n
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\n  \n 1977\n \n \n (4)\n \n \n
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\n \n\n \n \n Tikhonov, A. N.; and Arsenin, V.\n\n\n \n \n \n \n Solution of Ill-Posed Problems.\n \n \n \n\n\n \n\n\n\n V. H. Winston and Sons, Washington, DC, 1977.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@book{tikhonov1977,\n\taddress = {Washington, DC},\n\ttitle = {Solution of {Ill}-{Posed} {Problems}},\n\tpublisher = {V. H. Winston and Sons},\n\tauthor = {Tikhonov, A. N. and Arsenin, V.},\n\tyear = {1977},\n}\n\n\n\n
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\n \n\n \n \n Darden, C. M\n\n\n \n \n \n \n Sonic Boom Theory: Its Status in Prediction and Minimization.\n \n \n \n\n\n \n\n\n\n Journal of Aircraft, 14(6): 569–576. 1977.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{darden1977,\n\ttitle = {Sonic {Boom} {Theory}: {Its} {Status} in {Prediction} and {Minimization}},\n\tvolume = {14},\n\tdoi = {10.2514/3.58822},\n\tabstract = {This paper gives a brief review of the currently accepted understanding of sonic boom phenomena and describes the manner in which modified linearized theory and geometric acoustics are used to predict the sonic boom caused by a complex aircraft configuration. Minimization methods that have-evolved in recent years are discussed, with particular attention given to a method developed by Seebass and George for an isothermal atmosphere which was modified for the real atmosphere by Darden. An additional modification which permits the relaxation of the nose bluntness requirement in the defining aircraft also is discussed. Finally, an overview of current areas of sonic boom research is given.},\n\tnumber = {6},\n\tjournal = {Journal of Aircraft},\n\tauthor = {Darden, Christine M},\n\tyear = {1977},\n\tpages = {569--576},\n}\n\n\n\n
\n
\n\n\n
\n This paper gives a brief review of the currently accepted understanding of sonic boom phenomena and describes the manner in which modified linearized theory and geometric acoustics are used to predict the sonic boom caused by a complex aircraft configuration. Minimization methods that have-evolved in recent years are discussed, with particular attention given to a method developed by Seebass and George for an isothermal atmosphere which was modified for the real atmosphere by Darden. An additional modification which permits the relaxation of the nose bluntness requirement in the defining aircraft also is discussed. Finally, an overview of current areas of sonic boom research is given.\n
\n\n\n
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\n \n\n \n \n Gil, A; Segura, J; and Temme, N\n\n\n \n \n \n \n Numerical Methods for Special Functions.\n \n \n \n\n\n \n\n\n\n In 1977. \n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@inproceedings{gil1977,\n\ttitle = {Numerical {Methods} for {Special} {Functions}},\n\tauthor = {Gil, A and Segura, J and Temme, N},\n\tyear = {1977},\n}\n\n\n\n
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\n \n\n \n \n Panaras, A. G.\n\n\n \n \n \n \n High Speed Unsteady Seperation about Concave Bodies - a Physical Explanation.\n \n \n \n\n\n \n\n\n\n Technical Report 1977.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@techreport{panaras1977,\n\ttitle = {High {Speed} {Unsteady} {Seperation} about {Concave} {Bodies} - a {Physical} {Explanation}},\n\tauthor = {Panaras, A. G.},\n\tyear = {1977},\n}\n\n\n\n
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\n  \n 1976\n \n \n (3)\n \n \n
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\n \n\n \n \n Zucrow, M. J.; and Hoffman, J. D.\n\n\n \n \n \n \n Gas Dynamics.\n \n \n \n\n\n \n\n\n\n Volume 1 Wiley, 1976.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@book{zucrow1976,\n\ttitle = {Gas {Dynamics}},\n\tvolume = {1},\n\tpublisher = {Wiley},\n\tauthor = {Zucrow, M. J. and Hoffman, J. D.},\n\tyear = {1976},\n}\n\n\n\n
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\n \n\n \n \n \n\n\n \n \n \n \n \n U.S. Standard Atmosphere, 1976.\n \n \n \n \n\n\n \n\n\n\n 1976.\n \n\n\n\n
\n\n\n\n \n \n \"U.S.Paper\n  \n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@misc{atmosphere1976,\n\ttitle = {U.{S}. {Standard} {Atmosphere}, 1976},\n\turl = {https://www.ngdc.noaa.gov/stp/space-weather/online-publications/miscellaneous/us-standard-atmosphere-1976/us-standard-atmosphere_st76-1562_noaa.pdf},\n\tyear = {1976},\n}\n\n\n\n
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\n \n\n \n \n Ogilvie, J F; and Koo, D\n\n\n \n \n \n \n Dunham Potential Energy Coefficients of the Hydrogen Halides and Carbon Monoxide.\n \n \n \n\n\n \n\n\n\n Journal of Molecular Spectroscopy, 61(3): 332–336. 1976.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{ogilvie1976,\n\ttitle = {Dunham {Potential} {Energy} {Coefficients} of the {Hydrogen} {Halides} and {Carbon} {Monoxide}},\n\tvolume = {61},\n\tdoi = {10.1016/0022-2852(76)90323-4},\n\tnumber = {3},\n\tjournal = {Journal of Molecular Spectroscopy},\n\tauthor = {Ogilvie, J F and Koo, D},\n\tyear = {1976},\n\tpages = {332--336},\n}\n\n\n\n
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\n  \n 1975\n \n \n (4)\n \n \n
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\n \n\n \n \n Whitson, D. W.\n\n\n \n \n \n \n The Prevention of Electrical Breakdown and Electrostatic Voltage Problems in the Space Shuttle and its Payloads.\n \n \n \n\n\n \n\n\n\n Technical Report NASA-TM-81137, NASA, 1975.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@techreport{whitson1975,\n\ttype = {Technical {Memorandum}},\n\ttitle = {The {Prevention} of {Electrical} {Breakdown} and {Electrostatic} {Voltage} {Problems} in the {Space} {Shuttle} and its {Payloads}},\n\tnumber = {NASA-TM-81137},\n\tinstitution = {NASA},\n\tauthor = {Whitson, D. W.},\n\tyear = {1975},\n}\n\n\n\n
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\n \n\n \n \n Tiegerman, B.\n\n\n \n \n \n \n Sonic booms of drag dominated hypersonic vehicles.\n \n \n \n\n\n \n\n\n\n . 1975.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@article{tiegerman1975,\n\ttitle = {Sonic booms of drag dominated hypersonic vehicles},\n\tauthor = {Tiegerman, Bernard},\n\tyear = {1975},\n}\n\n\n\n
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\n \n\n \n \n Ericsson, L. E.\n\n\n \n \n \n \n \n Generalized unsteady embedded Newtonian flow.\n \n \n \n \n\n\n \n\n\n\n Journal of Spacecraft and Rockets, 12(12): 718–726. May 1975.\n \n\n\n\n
\n\n\n\n \n \n \"GeneralizedPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
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@article{ericsson1975,\n\ttitle = {Generalized unsteady embedded {Newtonian} flow},\n\tvolume = {12},\n\turl = {https://arc.aiaa.org/doi/10.2514/3.27870},\n\tdoi = {10.2514/3.27870},\n\tabstract = {An analysis is presented which extends the previously developed unsteady embedded Newtonian theory down to finite supersonic Mach numbers. It is found that Mach number can have a very large influence on the stability characteristics of slender blunted cones, and that there exist cone angle-nose bluntness combinations for which these Mach number effects are minimized. The computed effects of nose bluntness on static and dynamic stability derivatives are in excellent agreement with available experimental data. This also holds true for the highly nonlinear effects of angle of attack. © American Institute of Aeronautics and Astronautics, Inc., 1975, All rights reserved.},\n\tnumber = {12},\n\tjournal = {Journal of Spacecraft and Rockets},\n\tauthor = {Ericsson, Lars E.},\n\tmonth = may,\n\tyear = {1975},\n\tkeywords = {Aerodynamic Characteristics, Angle of Attack, Boundary Layer Transition, Dynamic Pressure, Dynamic Support Interference, Flow Characteristics, Hypersonic Flows, Mach Angle, Unsteady Aerodynamics, Wind Tunnel Tests},\n\tpages = {718--726},\n}\n\n\n\n
\n
\n\n\n
\n An analysis is presented which extends the previously developed unsteady embedded Newtonian theory down to finite supersonic Mach numbers. It is found that Mach number can have a very large influence on the stability characteristics of slender blunted cones, and that there exist cone angle-nose bluntness combinations for which these Mach number effects are minimized. The computed effects of nose bluntness on static and dynamic stability derivatives are in excellent agreement with available experimental data. This also holds true for the highly nonlinear effects of angle of attack. © American Institute of Aeronautics and Astronautics, Inc., 1975, All rights reserved.\n
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\n \n\n \n \n Stewart, R F\n\n\n \n \n \n \n A numerical study of coupled Hartree-Fock theory for open-shell systems.\n \n \n \n\n\n \n\n\n\n Molecular Physics, 30(4): 1283–1288. 1975.\n \n\n\n\n
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@article{stewart1975,\n\ttitle = {A numerical study of coupled {Hartree}-{Fock} theory for open-shell systems},\n\tvolume = {30},\n\tdoi = {10.1080/00268977500102811},\n\tnumber = {4},\n\tjournal = {Molecular Physics},\n\tauthor = {Stewart, R F},\n\tyear = {1975},\n\tpages = {1283--1288},\n}\n\n\n\n
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\n  \n 1974\n \n \n (2)\n \n \n
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\n \n\n \n \n Stollery, J. L.; and Bates, L.\n\n\n \n \n \n \n \n Turbulent hypersonic viscous interaction.\n \n \n \n \n\n\n \n\n\n\n Journal of Fluid Mechanics, 63(1): 145–156. 1974.\n Publisher: Cambridge University Press\n\n\n\n
\n\n\n\n \n \n \"TurbulentPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{stollery1974,\n\ttitle = {Turbulent hypersonic viscous interaction},\n\tvolume = {63},\n\turl = {https://doi.org/10.1017/S0022112074001054},\n\tdoi = {10.1017/S0022112074001054},\n\tabstract = {A theoretical analysis has been made of turbulent viscous interaction on iso-thermal surfaces at hypersonic speeds. The important parameters governing the effects of incidence and displacement have been obtained under both strong and weak interaction conditions for flat-plate flows. A more general expression relating boundary-layer growth to the external pressure field and effective body shape has been obtained. The method is applied to the wedge compression corner problem and the results compared with some experimental data. © 1974, Cambridge University Press. All rights reserved.},\n\tnumber = {1},\n\tjournal = {Journal of Fluid Mechanics},\n\tauthor = {Stollery, J. L. and Bates, L.},\n\tyear = {1974},\n\tnote = {Publisher: Cambridge University Press},\n\tpages = {145--156},\n}\n\n\n\n
\n
\n\n\n
\n A theoretical analysis has been made of turbulent viscous interaction on iso-thermal surfaces at hypersonic speeds. The important parameters governing the effects of incidence and displacement have been obtained under both strong and weak interaction conditions for flat-plate flows. A more general expression relating boundary-layer growth to the external pressure field and effective body shape has been obtained. The method is applied to the wedge compression corner problem and the results compared with some experimental data. © 1974, Cambridge University Press. All rights reserved.\n
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\n \n\n \n \n Green, K. S; and Putnam, T. W\n\n\n \n \n \n \n Measurements of Sonic Booms Generated by an Airplane Flying at Mach 3.5 and 4.8.\n \n \n \n\n\n \n\n\n\n Technical Report 1974.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@techreport{green1974,\n\ttitle = {Measurements of {Sonic} {Booms} {Generated} by an {Airplane} {Flying} at {Mach} 3.5 and 4.8},\n\tauthor = {Green, Karen S and Putnam, Terrill W},\n\tyear = {1974},\n}\n\n\n\n
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\n  \n 1973\n \n \n (3)\n \n \n
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\n \n\n \n \n Breen, J E; Quy, R B; and Glass, G P\n\n\n \n \n \n \n Vibrational relaxation of O\\textsubscript\\2\\ in the presence of atomic oxygen.\n \n \n \n\n\n \n\n\n\n The Journal of Chemical Physics, 59(1): 556–557. 1973.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@article{breen1973,\n\ttitle = {Vibrational relaxation of {O}{\\textbackslash}textsubscript\\{2\\} in the presence of atomic oxygen},\n\tvolume = {59},\n\tnumber = {1},\n\tjournal = {The Journal of Chemical Physics},\n\tauthor = {Breen, J E and Quy, R B and Glass, G P},\n\tyear = {1973},\n\tpages = {556--557},\n}\n\n\n\n
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\n \n\n \n \n Dunn, M. G.; and Kang, S.\n\n\n \n \n \n \n \n Theoretical and experimental studies of reentry plasmas.\n \n \n \n \n\n\n \n\n\n\n Technical Report 1973.\n \n\n\n\n
\n\n\n\n \n \n \"TheoreticalPaper\n  \n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@techreport{dunn1973,\n\ttitle = {Theoretical and experimental studies of reentry plasmas},\n\turl = {https://ntrs.nasa.gov/citations/19730013358},\n\tauthor = {Dunn, M. G. and Kang, S.},\n\tyear = {1973},\n}\n\n\n\n
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\n \n\n \n \n Shatalov, O P\n\n\n \n \n \n \n Molecular dissociation of oxygen in the absence of vibrational equilibrium.\n \n \n \n\n\n \n\n\n\n Combustion, Explosion and Shock Waves,610–613. 1973.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@article{shatalov1973,\n\ttitle = {Molecular dissociation of oxygen in the absence of vibrational equilibrium},\n\tjournal = {Combustion, Explosion and Shock Waves},\n\tauthor = {Shatalov, O P},\n\tyear = {1973},\n\tpages = {610--613},\n}\n\n\n\n
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\n  \n 1971\n \n \n (2)\n \n \n
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\n \n\n \n \n Breshears, W D; Bird, P F; and Kiefer, J H\n\n\n \n \n \n \n Density Gradient Measurements of O\\textsubscript\\2\\ Dissociation in Shock Waves.\n \n \n \n\n\n \n\n\n\n The Journal of Chemical Physics, 55(8). 1971.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@article{breshears1971,\n\ttitle = {Density {Gradient} {Measurements} of {O}{\\textbackslash}textsubscript\\{2\\} {Dissociation} in {Shock} {Waves}},\n\tvolume = {55},\n\tnumber = {8},\n\tjournal = {The Journal of Chemical Physics},\n\tauthor = {Breshears, W D and Bird, P F and Kiefer, J H},\n\tyear = {1971},\n}\n\n\n\n
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\n \n\n \n \n Blottner, F G; Johnson, M; and Ellis, M\n\n\n \n \n \n \n Chemically Reacting Viscous Flow Program for Multi-Component Gas Mixtures.\n \n \n \n\n\n \n\n\n\n Technical Report 1971.\n Issue: SC-RR-70-754\n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@techreport{blottner1971,\n\ttitle = {Chemically {Reacting} {Viscous} {Flow} {Program} for {Multi}-{Component} {Gas} {Mixtures}},\n\tauthor = {Blottner, F G and Johnson, M and Ellis, M},\n\tyear = {1971},\n\tdoi = {10.2172/4658539},\n\tnote = {Issue: SC-RR-70-754},\n}\n\n\n\n
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\n  \n 1970\n \n \n (4)\n \n \n
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\n \n\n \n \n McGhee, R.\n\n\n \n \n \n \n Jet-Plume-Induced Flow Separation on Axisymmetric Bodies at Mach Numbers of 3.00, 4.50, and 6.00.\n \n \n \n\n\n \n\n\n\n August 1970.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@misc{mcghee1970_1,\n\ttitle = {Jet-{Plume}-{Induced} {Flow} {Separation} on {Axisymmetric} {Bodies} at {Mach} {Numbers} of 3.00, 4.50, and 6.00},\n\tpublisher = {NASA},\n\tauthor = {McGhee, Robert},\n\tmonth = aug,\n\tyear = {1970},\n}\n\n\n\n
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\n \n\n \n \n McGhee, R.\n\n\n \n \n \n \n Jet-Plume-Induced Flow Separation on a Lifting Entry Body at Mach Numbers From 4.00 to 6.00.\n \n \n \n\n\n \n\n\n\n April 1970.\n \n\n\n\n
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@misc{mcghee1970_2,\n\ttitle = {Jet-{Plume}-{Induced} {Flow} {Separation} on a {Lifting} {Entry} {Body} at {Mach} {Numbers} {From} 4.00 to 6.00},\n\tpublisher = {NASA},\n\tauthor = {McGhee, Robert},\n\tmonth = apr,\n\tyear = {1970},\n}\n\n\n\n
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\n \n\n \n \n Seebass, A R.\n\n\n \n \n \n \n Hypersonic Boom.\n \n \n \n\n\n \n\n\n\n Technical Report 1970.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@techreport{seebass1970,\n\ttitle = {Hypersonic {Boom}},\n\tauthor = {Seebass, A R.},\n\tyear = {1970},\n}\n\n\n\n
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\n \n\n \n \n Weeks, T. M\n\n\n \n \n \n \n \n Effects of Flow Unsteadiness on Hypersonic Wind-Tunnel Spectroscopic Diagnostics.\n \n \n \n \n\n\n \n\n\n\n AIAA Journal, 8(8). 1970.\n \n\n\n\n
\n\n\n\n \n \n \"EffectsPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{weeks1970,\n\ttitle = {Effects of {Flow} {Unsteadiness} on {Hypersonic} {Wind}-{Tunnel} {Spectroscopic} {Diagnostics}},\n\tvolume = {8},\n\turl = {http://arc.aiaa.org},\n\tdoi = {10.2514/3.5926},\n\tabstract = {An analysis is presented of nonlinear effects of time varying flow properties on interpretation of spectroscopic measurements. Both direct emission as well as electron beam techniques are considered. A method, based on this analysis, is evolved whereby both average and mean square fluctuating temperatures can be obtained using conventional instrumentation. The method is applied to several selected experimental cases cited in the literature, including recent arc-heated hypersonic wind tunnel electron beam measurements. The theory is extended to include species number density fluctuations when temperature fluctuations are also present. Nomenclature A n m = spontaneous transition probability c = speed of light E m-electron energy level 0(vi) = vibrational term value (Nz X Is) g m = statistical weight h = Planck's constant / = line or band intensity k = Boltzmann's constant J£' = rotational quantum number q(v f ,v") = Franck-Condon factor R = line or band intensity ratio T = static temperature v = frequency B r = characteristic rotational temperature Subscripts e = excitation 0 = reference conditions r = rotational i) = vibrational},\n\tnumber = {8},\n\tjournal = {AIAA Journal},\n\tauthor = {Weeks, Thomas M},\n\tyear = {1970},\n}\n\n\n\n
\n
\n\n\n
\n An analysis is presented of nonlinear effects of time varying flow properties on interpretation of spectroscopic measurements. Both direct emission as well as electron beam techniques are considered. A method, based on this analysis, is evolved whereby both average and mean square fluctuating temperatures can be obtained using conventional instrumentation. The method is applied to several selected experimental cases cited in the literature, including recent arc-heated hypersonic wind tunnel electron beam measurements. The theory is extended to include species number density fluctuations when temperature fluctuations are also present. Nomenclature A n m = spontaneous transition probability c = speed of light E m-electron energy level 0(vi) = vibrational term value (Nz X Is) g m = statistical weight h = Planck's constant / = line or band intensity k = Boltzmann's constant J£' = rotational quantum number q(v f ,v\") = Franck-Condon factor R = line or band intensity ratio T = static temperature v = frequency B r = characteristic rotational temperature Subscripts e = excitation 0 = reference conditions r = rotational i) = vibrational\n
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\n  \n 1969\n \n \n (3)\n \n \n
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\n \n\n \n \n Anderson, J H B\n\n\n \n \n \n \n Experimental Determination of the Gladstone‐Dale Constants for Dissociating Oxygen.\n \n \n \n\n\n \n\n\n\n The Physics of Fluids, 12(5): I–60. 1969.\n \n\n\n\n
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\n 
@article{anderson1969,\n\ttitle = {Experimental {Determination} of the {Gladstone}‐{Dale} {Constants} for {Dissociating} {Oxygen}},\n\tvolume = {12},\n\tnumber = {5},\n\tjournal = {The Physics of Fluids},\n\tauthor = {Anderson, J H B},\n\tyear = {1969},\n\tpages = {I--60},\n}\n\n\n\n
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\n \n\n \n \n Hoag, D. G.\n\n\n \n \n \n \n Apollo Navigation, Guidance, and Control Systems: A Progress Report.\n \n \n \n\n\n \n\n\n\n Technical Report 1969.\n \n\n\n\n
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@techreport{hoag1969,\n\ttitle = {Apollo {Navigation}, {Guidance}, and {Control} {Systems}: {A} {Progress} {Report}},\n\tauthor = {Hoag, D. G.},\n\tyear = {1969},\n}\n\n\n\n
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\n \n\n \n \n Bortner, M H\n\n\n \n \n \n \n A Review of Rate Constants of Selected Reactions of Interest in Re-Entry Flow Fields in the Atmosphere.\n \n \n \n\n\n \n\n\n\n Technical Report May 1969.\n Issue: Technical Note 484\n\n\n\n
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@techreport{bortner1969,\n\ttitle = {A {Review} of {Rate} {Constants} of {Selected} {Reactions} of {Interest} in {Re}-{Entry} {Flow} {Fields} in the {Atmosphere}},\n\tauthor = {Bortner, M H},\n\tmonth = may,\n\tyear = {1969},\n\tnote = {Issue: Technical Note 484},\n}\n\n\n\n
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\n  \n 1968\n \n \n (3)\n \n \n
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\n \n\n \n \n Clayton, F.; Greene, R.; Kratsch, K.; Martinez, M.; and Wuerer, J.\n\n\n \n \n \n \n Graphite ablation in high-pressure environments.\n \n \n \n\n\n \n\n\n\n In Entry Vehicle Systems and Technology Meeting, Williamsburg,VA,U.S.A., December 1968. American Institute of Aeronautics and Astronautics\n \n\n\n\n
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\n 
@inproceedings{clayton_graphite_1968,\n\taddress = {Williamsburg,VA,U.S.A.},\n\ttitle = {Graphite ablation in high-pressure environments},\n\tdoi = {10.2514/6.1968-1153},\n\tlanguage = {en},\n\turldate = {2023-10-30},\n\tbooktitle = {Entry {Vehicle} {Systems} and {Technology} {Meeting}},\n\tpublisher = {American Institute of Aeronautics and Astronautics},\n\tauthor = {Clayton, F. and Greene, R. and Kratsch, K. and Martinez, M. and Wuerer, J.},\n\tmonth = dec,\n\tyear = {1968},\n}\n\n\n\n\n\n\n\n\n\n\n\n
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\n \n\n \n \n Calder, G V; and Ruedenberg, K.\n\n\n \n \n \n \n Quantitative Correlations between Rotational and Vibrational Spectroscopic Constants in Diatomic Molecules.\n \n \n \n\n\n \n\n\n\n The Journal of Chemical Physics, 49(12): 5399–5415. 1968.\n \n\n\n\n
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@article{calder1968,\n\ttitle = {Quantitative {Correlations} between {Rotational} and {Vibrational} {Spectroscopic} {Constants} in {Diatomic} {Molecules}},\n\tvolume = {49},\n\tdoi = {10.1063/1.1670065},\n\tnumber = {12},\n\tjournal = {The Journal of Chemical Physics},\n\tauthor = {Calder, G V and Ruedenberg, Klaus},\n\tyear = {1968},\n\tpages = {5399--5415},\n}\n\n\n\n
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\n \n\n \n \n Watts, J. D\n\n\n \n \n \n \n Flight Experience with Shock Impingement and Interference Heating on the X-15-2 Research Airplane.\n \n \n \n\n\n \n\n\n\n Technical Report 1968.\n Issue: NASA TM X-1669\n\n\n\n
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@techreport{watts1968,\n\ttitle = {Flight {Experience} with {Shock} {Impingement} and {Interference} {Heating} on the {X}-15-2 {Research} {Airplane}},\n\tauthor = {Watts, Joe D},\n\tyear = {1968},\n\tnote = {Issue: NASA TM X-1669},\n}\n\n\n\n
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\n  \n 1967\n \n \n (3)\n \n \n
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\n \n\n \n \n Kiefer, J H; and Lutz, R W\n\n\n \n \n \n \n The effect of oxygen atoms on the vibrational relaxation of oxygen.\n \n \n \n\n\n \n\n\n\n Symposium (International) on Combustion, 11(1): 67–76. 1967.\n \n\n\n\n
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\n 
@article{kiefer1967,\n\ttitle = {The effect of oxygen atoms on the vibrational relaxation of oxygen},\n\tvolume = {11},\n\tnumber = {1},\n\tjournal = {Symposium (International) on Combustion},\n\tauthor = {Kiefer, J H and Lutz, R W},\n\tyear = {1967},\n\tpages = {67--76},\n}\n\n\n\n
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\n \n\n \n \n Smithells, C J\n\n\n \n \n \n \n Metals Reference Book.\n \n \n \n\n\n \n\n\n\n Plenum Press, 4th edition, 1967.\n \n\n\n\n
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@book{smithells1967,\n\tedition = {4th},\n\ttitle = {Metals {Reference} {Book}},\n\tpublisher = {Plenum Press},\n\tauthor = {Smithells, C J},\n\tyear = {1967},\n}\n\n\n\n
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\n \n\n \n \n Hobbs, G. D.; and Wesson, J. A.\n\n\n \n \n \n \n \n Heat flow through a Langmuir sheath in the presence of electron emission.\n \n \n \n \n\n\n \n\n\n\n Plasma Physics, 9(1): 85–85. January 1967.\n Publisher: IOP Publishing\n\n\n\n
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\n 
@article{hobbs1967,\n\ttitle = {Heat flow through a {Langmuir} sheath in the presence of electron emission},\n\tvolume = {9},\n\turl = {https://iopscience.iop.org/article/10.1088/0032-1028/9/1/410},\n\tdoi = {10.1088/0032-1028/9/1/410},\n\tnumber = {1},\n\tjournal = {Plasma Physics},\n\tauthor = {Hobbs, G. D. and Wesson, J. A.},\n\tmonth = jan,\n\tyear = {1967},\n\tnote = {Publisher: IOP Publishing},\n\tpages = {85--85},\n}\n\n\n\n
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\n  \n 1966\n \n \n (2)\n \n \n
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\n \n\n \n \n Sutton, W.\n\n\n \n \n \n \n Direct energy conversion.\n \n \n \n\n\n \n\n\n\n McGraw-Hill Book Company, 1966.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
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@book{sutton1966,\n\ttitle = {Direct energy conversion},\n\tpublisher = {McGraw-Hill Book Company},\n\tauthor = {Sutton, W.},\n\tyear = {1966},\n\tkeywords = {* - direct energy conversion- mhd generators, - fuel cells, - solar energy conversion- photovoltaic conversion, - thermionic converters, - thermoelectric generators, conversion, design, direct energy conversion, direct energy converters, electric batteries, electricity, electrochemical cells, energy, energy conversion, energy storage systems, fluid mechanics, fuel cells, hydrodynamics, magnetohydrodynamics, mechanics, mhd generators, nesdps office of nuclear energy space and defense, operation, production, solar energy, thermionics, thermoelectric generators},\n}\n\n\n\n
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\n \n\n \n \n Mirels, H.\n\n\n \n \n \n \n Correlation Formulas for Laminar Shock Tube Boundary Layer.\n \n \n \n\n\n \n\n\n\n The Physics of Fluids, 9(7): 1265–1272. July 1966.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{mirels1966,\n\ttitle = {Correlation {Formulas} for {Laminar} {Shock} {Tube} {Boundary} {Layer}},\n\tvolume = {9},\n\tissn = {0031-9171},\n\tdoi = {10.1063/1.1761839},\n\tabstract = {The laminar boundary layer behind a moving shock is studied. The major objective is to obtain improved correlation formulas (valid for large W, where W is the density ratio across the shock) and to simplify the procedure for obtaining boundary-layer parameters. Numerical solutions for shear, heat transfer, and boundary-layer thicknesses are presented for 1 ≤ W ≤ ∞, σ = 0.67, 0.72, and 1.0 (σ is the Prandtl number) assuming constant ρμ (ρ is the density and μ, the viscosity) and an ideal gas. Correlation formulas are obtained which agree with these numerical results to within fractions of a percent. Approximate corrections for variable ρμ and real-gas effects are then introduced. Charts and tables are presented which describe boundary layers in air (Ms ≤ 22) and argon (Ms ≤ 10).},\n\tlanguage = {en},\n\tnumber = {7},\n\turldate = {2023-09-07},\n\tjournal = {The Physics of Fluids},\n\tauthor = {Mirels, H.},\n\tmonth = jul,\n\tyear = {1966},\n\tpages = {1265--1272},\n}\n\n\n\n\n\n\n\n\n\n\n\n
\n
\n\n\n
\n The laminar boundary layer behind a moving shock is studied. The major objective is to obtain improved correlation formulas (valid for large W, where W is the density ratio across the shock) and to simplify the procedure for obtaining boundary-layer parameters. Numerical solutions for shear, heat transfer, and boundary-layer thicknesses are presented for 1 ≤ W ≤ ∞, σ = 0.67, 0.72, and 1.0 (σ is the Prandtl number) assuming constant ρμ (ρ is the density and μ, the viscosity) and an ideal gas. Correlation formulas are obtained which agree with these numerical results to within fractions of a percent. Approximate corrections for variable ρμ and real-gas effects are then introduced. Charts and tables are presented which describe boundary layers in air (Ms ≤ 22) and argon (Ms ≤ 10).\n
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\n  \n 1965\n \n \n (3)\n \n \n
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\n \n \n
\n \n\n \n \n Thomas, P D\n\n\n \n \n \n \n Transparency Assumption in Hypersonic Radiative Gas Dynamics.\n \n \n \n\n\n \n\n\n\n AIAA Journal, 3(8): 1401–1407. 1965.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{thomas1965,\n\ttitle = {Transparency {Assumption} in {Hypersonic} {Radiative} {Gas} {Dynamics}},\n\tvolume = {3},\n\tnumber = {8},\n\tjournal = {AIAA Journal},\n\tauthor = {Thomas, P D},\n\tyear = {1965},\n\tpages = {1401--1407},\n}\n\n\n\n
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\n \n\n \n \n Carlson, H. W; Mack, R. J; and Morris, O. A\n\n\n \n \n \n \n A Wind-Tunnel Investigation of the Effect of Body Shape on Sonic-Boom Pressure Distributions.\n \n \n \n\n\n \n\n\n\n Technical Report 1965.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@techreport{carlson1965,\n\ttitle = {A {Wind}-{Tunnel} {Investigation} of the {Effect} of {Body} {Shape} on {Sonic}-{Boom} {Pressure} {Distributions}},\n\tauthor = {Carlson, Harry W and Mack, Robert J and Morris, Odell A},\n\tyear = {1965},\n}\n\n\n\n
\n
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\n \n\n \n \n Touryan, K J\n\n\n \n \n \n \n A Hypersonic Plasma Power Generator.\n \n \n \n\n\n \n\n\n\n AIAA Journal, 3(4). 1965.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n\n\n\n
\n 
@article{touryan1965,\n\ttitle = {A {Hypersonic} {Plasma} {Power} {Generator}},\n\tvolume = {3},\n\tdoi = {10.2514/3.2942},\n\tabstract = {Theoretical and experimental analyses are presented which describe the operation and characteristics of a hypersonic plasma generator. The nose cone of a re-entry vehicle serves as a thermionic emitter of electrons (a cathode). These electrons are then conducted through the shock ionized air stream, increased in kinetic energy by collisions, and collected over the relatively cool vehicle afterbody, which is electrically insulated from the nose cone and which serves as an anode, or collector. A load connected between the cathode and anode within the vehicle completes the circuit. The generator operates basically as a plasma thermocouple and, for its power output, depends primarily on the large temperature and area differences between emitter and collector, with the kinetic energy of the plasma electrons as its energy source. Experiments in a plasma tunnel facility have yielded currents up to 30 amp/in. 2 of emitter area (pyrographite or graphite surfaces) under short-circuit and fully charge-neutralized conditions and 4.0 v open-circuit voltage and 1-ev plasma electron temperatures (16 w/in. 2 power output). Conditions for optimum output are discussed and estimates made for full-size re-entry vehicles on the basis of detailed re-entry trajectory calculations. A = A e (or Aem), A c = C = Ci = D = E = e = h = 7 = i = i m = j or J = k = I = m e , mi = n e , ni = r T T e , Tem, T c v V V T a. • E X 0 0 p},\n\tnumber = {4},\n\tjournal = {AIAA Journal},\n\tauthor = {Touryan, K J},\n\tyear = {1965},\n\tkeywords = {etc},\n}\n\n\n\n
\n
\n\n\n
\n Theoretical and experimental analyses are presented which describe the operation and characteristics of a hypersonic plasma generator. The nose cone of a re-entry vehicle serves as a thermionic emitter of electrons (a cathode). These electrons are then conducted through the shock ionized air stream, increased in kinetic energy by collisions, and collected over the relatively cool vehicle afterbody, which is electrically insulated from the nose cone and which serves as an anode, or collector. A load connected between the cathode and anode within the vehicle completes the circuit. The generator operates basically as a plasma thermocouple and, for its power output, depends primarily on the large temperature and area differences between emitter and collector, with the kinetic energy of the plasma electrons as its energy source. Experiments in a plasma tunnel facility have yielded currents up to 30 amp/in. 2 of emitter area (pyrographite or graphite surfaces) under short-circuit and fully charge-neutralized conditions and 4.0 v open-circuit voltage and 1-ev plasma electron temperatures (16 w/in. 2 power output). Conditions for optimum output are discussed and estimates made for full-size re-entry vehicles on the basis of detailed re-entry trajectory calculations. A = A e (or Aem), A c = C = Ci = D = E = e = h = 7 = i = i m = j or J = k = I = m e , mi = n e , ni = r T T e , Tem, T c v V V T a. • E X 0 0 p\n
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\n  \n 1964\n \n \n (6)\n \n \n
\n
\n \n \n
\n \n\n \n \n Mirels, H.\n\n\n \n \n \n \n Shock tube test time limitation due to turbulent wall boundary layer.\n \n \n \n\n\n \n\n\n\n AIAA Journal, 2(1): 84–93. January 1964.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{mirels1964,\n\ttitle = {Shock tube test time limitation due to turbulent wall boundary layer},\n\tvolume = {2},\n\tissn = {0001-1452, 1533-385X},\n\tdoi = {10.2514/3.2218},\n\tlanguage = {en},\n\tnumber = {1},\n\turldate = {2023-09-07},\n\tjournal = {AIAA Journal},\n\tauthor = {Mirels, Harold},\n\tmonth = jan,\n\tyear = {1964},\n\tpages = {84--93},\n}\n\n\n\n\n\n\n\n\n\n\n\n
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\n \n\n \n \n Robinson, C A; and McNab, I R\n\n\n \n \n \n \n \n Viscosity of Partially Ionized Gaseous Cesium.\n \n \n \n \n\n\n \n\n\n\n Journal of Applied Physics, 35(6): 1742–1745. 1964.\n \n\n\n\n
\n\n\n\n \n \n \"ViscosityPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{robinson1964,\n\ttitle = {Viscosity of {Partially} {Ionized} {Gaseous} {Cesium}},\n\tvolume = {35},\n\turl = {https://doi.org/10.1063/1.1713730},\n\tdoi = {10.1063/1.1713730},\n\tnumber = {6},\n\tjournal = {Journal of Applied Physics},\n\tauthor = {Robinson, C A and McNab, I R},\n\tyear = {1964},\n\tpages = {1742--1745},\n}\n\n\n\n
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\n \n\n \n \n Leblanc, A. R.; and Grannemann, W. W.\n\n\n \n \n \n \n Thermionic Generator for Re-Entry Vehicles.\n \n \n \n\n\n \n\n\n\n Proceedings of the IEEE, 52(11): 1302–1310. 1964.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{leblanc1964,\n\ttitle = {Thermionic {Generator} for {Re}-{Entry} {Vehicles}},\n\tvolume = {52},\n\tdoi = {10.1109/PROC.1964.3366},\n\tabstract = {A novel design of a thermionic generator for use on re-entry vehicles is analyzed analytically and experimentally. Equa-tions are derived for prediction of the output current, output power, and conditions of maximum power for the device. The electrical power output potential of a typical re-entry vehicle is obtained by solving the temperature history of a thin-walled emitter. Given the wall temperature and the work function, the saturated Richardson current is easily obtained. Other parameters needed for predicting output power are obtained from curves in the literature. To simulate re-entry conditions, a test model was built and in-serted in either a nitrogen or argon plasma jet. Graphite, thoriated tungsten, tungsten and molybdenum were used for the emitter and collector. Of the materials tested, graphite was the only material that met, to some degree, the qualifications needed for operation of the hypersonic plasma thermionic generator. Copyright © 1964 by The Institute of Electrical and Electronics Engineers, Inc.},\n\tnumber = {11},\n\tjournal = {Proceedings of the IEEE},\n\tauthor = {Leblanc, A. R. and Grannemann, W. W.},\n\tyear = {1964},\n\tpages = {1302--1310},\n}\n\n\n\n
\n
\n\n\n
\n A novel design of a thermionic generator for use on re-entry vehicles is analyzed analytically and experimentally. Equa-tions are derived for prediction of the output current, output power, and conditions of maximum power for the device. The electrical power output potential of a typical re-entry vehicle is obtained by solving the temperature history of a thin-walled emitter. Given the wall temperature and the work function, the saturated Richardson current is easily obtained. Other parameters needed for predicting output power are obtained from curves in the literature. To simulate re-entry conditions, a test model was built and in-serted in either a nitrogen or argon plasma jet. Graphite, thoriated tungsten, tungsten and molybdenum were used for the emitter and collector. Of the materials tested, graphite was the only material that met, to some degree, the qualifications needed for operation of the hypersonic plasma thermionic generator. Copyright © 1964 by The Institute of Electrical and Electronics Engineers, Inc.\n
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\n \n\n \n \n Touryan, K J\n\n\n \n \n \n \n The hypersonic plasma converter II.\n \n \n \n\n\n \n\n\n\n Technical Report 1964.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@techreport{touryan1964,\n\ttitle = {The hypersonic plasma converter {II}},\n\tauthor = {Touryan, K J},\n\tyear = {1964},\n}\n\n\n\n
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\n \n\n \n \n Lenard, M.\n\n\n \n \n \n \n Ionization of Cesium and Sodium Contaminated Air in the Hypersonic Slender Body Boundary Layer.\n \n \n \n\n\n \n\n\n\n Technical Report 1964.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@techreport{lenard1964,\n\ttitle = {Ionization of {Cesium} and {Sodium} {Contaminated} {Air} in the {Hypersonic} {Slender} {Body} {Boundary} {Layer}},\n\tauthor = {Lenard, M{\\textgreater}},\n\tyear = {1964},\n}\n\n\n\n
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\n \n\n \n \n Barker, J A; Fock, W; and Smith, F\n\n\n \n \n \n \n \n Calculation of Gas Transport Properties and the Interaction of Argon Atoms.\n \n \n \n \n\n\n \n\n\n\n The Physics of Fluids, 7(6): 897–903. 1964.\n \n\n\n\n
\n\n\n\n \n \n \"CalculationPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{barker1964,\n\ttitle = {Calculation of {Gas} {Transport} {Properties} and the {Interaction} of {Argon} {Atoms}},\n\tvolume = {7},\n\turl = {https://aip.scitation.org/doi/abs/10.1063/1.1711301},\n\tdoi = {10.1063/1.1711301},\n\tnumber = {6},\n\tjournal = {The Physics of Fluids},\n\tauthor = {Barker, J A and Fock, W and Smith, F},\n\tyear = {1964},\n\tpages = {897--903},\n}\n\n\n\n
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\n  \n 1963\n \n \n (2)\n \n \n
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\n \n\n \n \n White, D R; and Millikan, R C\n\n\n \n \n \n \n Vibrational Relaxation of Oxygen.\n \n \n \n\n\n \n\n\n\n The Journal of Chemical Physics, 39: 1803–1806. 1963.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{white1963,\n\ttitle = {Vibrational {Relaxation} of {Oxygen}},\n\tvolume = {39},\n\tjournal = {The Journal of Chemical Physics},\n\tauthor = {White, D R and Millikan, R C},\n\tyear = {1963},\n\tpages = {1803--1806},\n}\n\n\n\n
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\n \n\n \n \n Millikan, R C; and White, D R\n\n\n \n \n \n \n Systematics of Vibrational Relaxation.\n \n \n \n\n\n \n\n\n\n Journal of Chemical Physics, 39(1): 98–101. 1963.\n \n\n\n\n
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\n 
@article{millikan1963,\n\ttitle = {Systematics of {Vibrational} {Relaxation}},\n\tvolume = {39},\n\tnumber = {1},\n\tjournal = {Journal of Chemical Physics},\n\tauthor = {Millikan, R C and White, D R},\n\tyear = {1963},\n\tpages = {98--101},\n}\n\n\n\n
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\n  \n 1962\n \n \n (4)\n \n \n
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\n \n\n \n \n Wray, K L\n\n\n \n \n \n \n Shock‐Tube Study of the Coupling of the O\\textsubscript\\2\\-Ar Rates of Dissociation and Vibrational Relaxation.\n \n \n \n\n\n \n\n\n\n The Journal of Chemical Physics, 37(6). 1962.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@article{wray1962,\n\ttitle = {Shock‐{Tube} {Study} of the {Coupling} of the {O}{\\textbackslash}textsubscript\\{2\\}-{Ar} {Rates} of {Dissociation} and {Vibrational} {Relaxation}},\n\tvolume = {37},\n\tnumber = {6},\n\tjournal = {The Journal of Chemical Physics},\n\tauthor = {Wray, K L},\n\tyear = {1962},\n}\n\n\n\n
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\n \n\n \n \n Seiff, A.\n\n\n \n \n \n \n Secondary Flow-Fields Embedded in Hypersonic Shock Layers.\n \n \n \n\n\n \n\n\n\n Technical Report 1962.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@techreport{seiff1962,\n\ttitle = {Secondary {Flow}-{Fields} {Embedded} in {Hypersonic} {Shock} {Layers}},\n\tauthor = {Seiff, A.},\n\tyear = {1962},\n}\n\n\n\n
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\n \n\n \n \n Seiff, A.; and Whiting, E. E.\n\n\n \n \n \n \n Correlation of the Bow-Wave Profiles of Blunt Bodies.\n \n \n \n\n\n \n\n\n\n Technical Report 1962.\n \n\n\n\n
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@techreport{seiff1962a,\n\ttitle = {Correlation of the {Bow}-{Wave} {Profiles} of {Blunt} {Bodies}},\n\tauthor = {Seiff, A. and Whiting, E. E.},\n\tyear = {1962},\n}\n\n\n\n
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\n \n\n \n \n Losev, S A; and Generalov, N A\n\n\n \n \n \n \n A study of the excitation of vibrations and dissociation of oxygen molecules at high temperatures.\n \n \n \n\n\n \n\n\n\n Soviet Physics Doklady, 6. 1962.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@article{losev1962,\n\ttitle = {A study of the excitation of vibrations and dissociation of oxygen molecules at high temperatures},\n\tvolume = {6},\n\tjournal = {Soviet Physics Doklady},\n\tauthor = {Losev, S A and Generalov, N A},\n\tyear = {1962},\n}\n\n\n\n
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\n  \n 1961\n \n \n (4)\n \n \n
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\n \n\n \n \n Tatarski, V I\n\n\n \n \n \n \n Wave Propagation in a Turbulent Medium.\n \n \n \n\n\n \n\n\n\n McGraw-Hill, 1961.\n \n\n\n\n
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@book{tatarski1961,\n\ttitle = {Wave {Propagation} in a {Turbulent} {Medium}},\n\tpublisher = {McGraw-Hill},\n\tauthor = {Tatarski, V I},\n\tyear = {1961},\n}\n\n\n\n
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\n \n\n \n \n Camac, M; and Vaughan, A\n\n\n \n \n \n \n O\\textsubscript\\2\\ Dissociation Rates in O\\textsubscript\\2\\-Ar Mixtures.\n \n \n \n\n\n \n\n\n\n The Journal of Chemical Physics, 34(2). 1961.\n \n\n\n\n
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@article{camac1961,\n\ttitle = {O{\\textbackslash}textsubscript\\{2\\} {Dissociation} {Rates} in {O}{\\textbackslash}textsubscript\\{2\\}-{Ar} {Mixtures}},\n\tvolume = {34},\n\tnumber = {2},\n\tjournal = {The Journal of Chemical Physics},\n\tauthor = {Camac, M and Vaughan, A},\n\tyear = {1961},\n}\n\n\n\n
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\n \n\n \n \n Schexnayder, C J; and Evans, J S\n\n\n \n \n \n \n Measurements of the Dissociation Rate of Molecular Oxygen.\n \n \n \n\n\n \n\n\n\n Technical Report 1961.\n Issue: NASA TR R-108\n\n\n\n
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@techreport{schexnayder1961,\n\ttitle = {Measurements of the {Dissociation} {Rate} of {Molecular} {Oxygen}},\n\tauthor = {Schexnayder, C J and Evans, J S},\n\tyear = {1961},\n\tnote = {Issue: NASA TR R-108},\n}\n\n\n\n
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\n \n\n \n \n Seiff, A.; and Whiting, E. E.\n\n\n \n \n \n \n Calculation of Flow Fields from Bow- Wave Profiles for the Downstream Region of Blunt-Nosed Circular Cylinders in Axial Hypersonic Flight.\n \n \n \n\n\n \n\n\n\n Technical Report 1961.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@techreport{seiff1961,\n\ttitle = {Calculation of {Flow} {Fields} from {Bow}- {Wave} {Profiles} for the {Downstream} {Region} of {Blunt}-{Nosed} {Circular} {Cylinders} in {Axial} {Hypersonic} {Flight}},\n\tauthor = {Seiff, A. and Whiting, E. E.},\n\tyear = {1961},\n}\n\n\n\n
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\n  \n 1960\n \n \n (2)\n \n \n
\n
\n \n \n
\n \n\n \n \n Eckert, E. R. G.\n\n\n \n \n \n \n Survey of Boundary Layer Heat Transfer at High Velocities and High Temperatures.\n \n \n \n\n\n \n\n\n\n Technical Report University of Minnesota - Heat Transfer Lab, 1960.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@techreport{eckert1960,\n\ttitle = {Survey of {Boundary} {Layer} {Heat} {Transfer} at {High} {Velocities} and {High} {Temperatures}},\n\tinstitution = {University of Minnesota - Heat Transfer Lab},\n\tauthor = {Eckert, Enrst Rudolf Georg},\n\tyear = {1960},\n}\n\n\n\n
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\n \n\n \n \n Chernov, L A\n\n\n \n \n \n \n Wave Propagation in a Random Medium.\n \n \n \n\n\n \n\n\n\n McGraw-Hill, New York, 1960.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@book{chernov1960,\n\taddress = {New York},\n\ttitle = {Wave {Propagation} in a {Random} {Medium}},\n\tpublisher = {McGraw-Hill},\n\tauthor = {Chernov, L A},\n\tyear = {1960},\n}\n\n\n\n
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\n  \n 1959\n \n \n (2)\n \n \n
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\n \n \n
\n \n\n \n \n Alpher, R. A; and White, D. R\n\n\n \n \n \n \n Optical Refractivity of High‐Temperature Gases. I. Effects Resulting from Dissociation of Diatomic Gases.\n \n \n \n\n\n \n\n\n\n The Physics of Fluids, 2(2): 153–161. 1959.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{alpher1959,\n\ttitle = {Optical {Refractivity} of {High}‐{Temperature} {Gases}. {I}. {Effects} {Resulting} from {Dissociation} of {Diatomic} {Gases}},\n\tvolume = {2},\n\tnumber = {2},\n\tjournal = {The Physics of Fluids},\n\tauthor = {Alpher, Ralph A and White, Donald R},\n\tyear = {1959},\n\tpages = {153--161},\n}\n\n\n\n
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\n \n\n \n \n Crawford, D. H.\n\n\n \n \n \n \n Investigation of the Flow over a Spiked-Nose Hemisphere Cylinder at a Mach Number of 6.8.\n \n \n \n\n\n \n\n\n\n Technical Report 1959.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@techreport{crawford1959,\n\ttitle = {Investigation of the {Flow} over a {Spiked}-{Nose} {Hemisphere} {Cylinder} at a {Mach} {Number} of 6.8},\n\tauthor = {Crawford, Davis H.},\n\tyear = {1959},\n}\n\n\n\n
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\n  \n 1958\n \n \n (1)\n \n \n
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\n \n\n \n \n Fay, J.; and Riddell, F. R.\n\n\n \n \n \n \n Theory of Stagnation Point Heat Transfer in Dissociated Air.\n \n \n \n\n\n \n\n\n\n Journal of the Aerospace Sciences, 25(2): 73–85. February 1958.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{fay1958,\n\ttitle = {Theory of {Stagnation} {Point} {Heat} {Transfer} in {Dissociated} {Air}},\n\tvolume = {25},\n\tdoi = {10.2514/8.7517},\n\tabstract = {applicability for this approach.},\n\tnumber = {2},\n\tjournal = {Journal of the Aerospace Sciences},\n\tauthor = {Fay, J.A. and Riddell, F. R.},\n\tmonth = feb,\n\tyear = {1958},\n\tkeywords = {Aerodynamics, Atomic Diffusion, Boundary Layer Equations, Heat Transfer Measurements, Hypersonic Viscous Flow, Kinematic Viscosity, Prandtl Number, Stagnation Temperature, Thermal Diffusivity, Universal Gas Constant},\n\tpages = {73--85},\n}\n\n\n\n
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\n applicability for this approach.\n
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\n  \n 1957\n \n \n (3)\n \n \n
\n
\n \n \n
\n \n\n \n \n Kemp, N. H.; and Riddell, F. R.\n\n\n \n \n \n \n Heat Transfer to Satellite Vehicles Re-entering the Atmosphere.\n \n \n \n\n\n \n\n\n\n Journal of Jet Propulsion, 27(2): 132–137. 1957.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{kemp1957,\n\ttitle = {Heat {Transfer} to {Satellite} {Vehicles} {Re}-entering the {Atmosphere}},\n\tvolume = {27},\n\tdoi = {10.2514/8.12603},\n\tnumber = {2},\n\turldate = {2024-04-22},\n\tjournal = {Journal of Jet Propulsion},\n\tauthor = {Kemp, N. H. and Riddell, F. R.},\n\tyear = {1957},\n\tpages = {132--137},\n}\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n
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\n \n\n \n \n Mirels, H.\n\n\n \n \n \n \n Attenuation in a Shock Tube due to Unsteady-Boundary-Layer Action.\n \n \n \n\n\n \n\n\n\n Technical Report 1333, National Advisory Committee for Aeronautics, 1957.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@techreport{mirels1957,\n\ttitle = {Attenuation in a {Shock} {Tube} due to {Unsteady}-{Boundary}-{Layer} {Action}},\n\tnumber = {1333},\n\tinstitution = {National Advisory Committee for Aeronautics},\n\tauthor = {Mirels, Harold},\n\tyear = {1957},\n}\n\n\n\n
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\n \n\n \n \n Lees, L.; and Kubota, T.\n\n\n \n \n \n \n \n Inviscid Hypersonic Flow Over Blunt-Nosed Slender Bodies.\n \n \n \n \n\n\n \n\n\n\n Journal of the Aeronautical Sciences, 24(3): 195–202. March 1957.\n Publisher: American Institute of Aeronautics and Astronautics (AIAA)\n\n\n\n
\n\n\n\n \n \n \"InviscidPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n
\n 
@article{lees1957,\n\ttitle = {Inviscid {Hypersonic} {Flow} {Over} {Blunt}-{Nosed} {Slender} {Bodies}},\n\tvolume = {24},\n\turl = {https://arc.aiaa.org/doi/abs/10.2514/8.3803},\n\tdoi = {10.2514/8.3803},\n\tnumber = {3},\n\tjournal = {Journal of the Aeronautical Sciences},\n\tauthor = {Lees, Lester and Kubota, Toshi},\n\tmonth = mar,\n\tyear = {1957},\n\tnote = {Publisher: American Institute of Aeronautics and Astronautics (AIAA)},\n\tkeywords = {Air Transportation, Angle of Attack, Drag Coefficient, Guggenheim Aeronautical Laboratory, Hypersonic Speed, Hypersonic Wind Tunnels, Inviscid Hypersonic Flow, Leading Edges, Pressure Coefficient, Shock Wave Interaction},\n\tpages = {195--202},\n}\n\n\n\n
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\n  \n 1956\n \n \n (4)\n \n \n
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\n \n \n
\n \n\n \n \n Mirels, H.\n\n\n \n \n \n \n Boundary Layer Behind Shock or Thin Expansion Wave Moving into Stationary Fluid.\n \n \n \n\n\n \n\n\n\n Technical Report 3712, National Advisory Committee for Aeronautics, 1956.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@techreport{mirels1956,\n\ttitle = {Boundary {Layer} {Behind} {Shock} or {Thin} {Expansion} {Wave} {Moving} into {Stationary} {Fluid}},\n\tnumber = {3712},\n\tinstitution = {National Advisory Committee for Aeronautics},\n\tauthor = {Mirels, Harold},\n\tyear = {1956},\n}\n\n\n\n
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\n \n\n \n \n Ashley, H.; and Zartarian, G.\n\n\n \n \n \n \n Piston Theory-A New Aerodynamic Tool for the Aeroelastician.\n \n \n \n\n\n \n\n\n\n Journal of the Aeronautical Sciences, 23(12): 1109–1118. 1956.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{ashley1956,\n\ttitle = {Piston {Theory}-{A} {New} {Aerodynamic} {Tool} for the {Aeroelastician}},\n\tvolume = {23},\n\tdoi = {10.2514/8.3740},\n\tnumber = {12},\n\turldate = {2023-08-03},\n\tjournal = {Journal of the Aeronautical Sciences},\n\tauthor = {Ashley, Holt and Zartarian, Garabed},\n\tyear = {1956},\n\tpages = {1109--1118},\n}\n\n\n\n\n\n\n\n
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\n \n\n \n \n Murphy, E. L.; and R. H. Good, J.\n\n\n \n \n \n \n Thermionic Emission, Field Emission, and the Transition Region.\n \n \n \n\n\n \n\n\n\n Physical Review, 102(6). 1956.\n Publisher: American Physical Society\n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{murphy1956,\n\ttitle = {Thermionic {Emission}, {Field} {Emission}, and the {Transition} {Region}},\n\tvolume = {102},\n\tdoi = {10.1103/PhysRev.102.1464},\n\tabstract = {Although the theories of thermionic and field emission of electrons from metals are very well understood, the two types of emission have usually been studied separately by first specifying the range of temperature and field and then constructing the appropriate expression for the current. In this paper the emission is treated from a unified point of view in order to establish the ranges of temperature and field for the two types of emission and to investigate the current in the region intermediate between thermionic and field emission. A general expression for the emitted current as a function of field, temperature, and work function is set up in the form of a definite integral. Each type of emission is then associated with a technique for approximating the integral and with a characteristic dependence on the three parameters. An approximation for low fields and high temperatures leads to an extension of the Richardson-Schottky formula for thermionic emission. The values of temperature and field for which it applies are established by considering the validity of the approximation. An analogous treatment of the integral, for high fields and low temperatures, gives an extension of the Fowler-Nordheim formula for field emission, and establishes the region of temperature and field in which it applies. Also another approximate method for evaluating the integral is given which leads to a new type of dependence of the emitted current on temperature and field and which applies in a narrow region of temperature and field intermediate between the field and thermionic emission regions. © 1956 The American Physical Society.},\n\tnumber = {6},\n\tjournal = {Physical Review},\n\tauthor = {Murphy, E. L. and R. H. Good, Jr},\n\tyear = {1956},\n\tnote = {Publisher: American Physical Society},\n}\n\n\n\n
\n
\n\n\n
\n Although the theories of thermionic and field emission of electrons from metals are very well understood, the two types of emission have usually been studied separately by first specifying the range of temperature and field and then constructing the appropriate expression for the current. In this paper the emission is treated from a unified point of view in order to establish the ranges of temperature and field for the two types of emission and to investigate the current in the region intermediate between thermionic and field emission. A general expression for the emitted current as a function of field, temperature, and work function is set up in the form of a definite integral. Each type of emission is then associated with a technique for approximating the integral and with a characteristic dependence on the three parameters. An approximation for low fields and high temperatures leads to an extension of the Richardson-Schottky formula for thermionic emission. The values of temperature and field for which it applies are established by considering the validity of the approximation. An analogous treatment of the integral, for high fields and low temperatures, gives an extension of the Fowler-Nordheim formula for field emission, and establishes the region of temperature and field in which it applies. Also another approximate method for evaluating the integral is given which leads to a new type of dependence of the emitted current on temperature and field and which applies in a narrow region of temperature and field intermediate between the field and thermionic emission regions. © 1956 The American Physical Society.\n
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\n \n\n \n \n Whitham, G. B.\n\n\n \n \n \n \n \n On the propagation of weak shock waves.\n \n \n \n \n\n\n \n\n\n\n Journal of Fluid Mechanics, 1(3): 290–318. 1956.\n Publisher: Cambridge University Press\n\n\n\n
\n\n\n\n \n \n \"OnPaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{whitham1956,\n\ttitle = {On the propagation of weak shock waves},\n\tvolume = {1},\n\turl = {https://doi.org/10.1017/S0022112056000172},\n\tdoi = {10.1017/S0022112056000172},\n\tabstract = {A method is presented for treating problems of the propagation and ultimate decay of the shocks produced by explosions and by bodies in supersonic flight. The theory is restricted to weak shocks, but is of quite general application within that limitation. In the author's earlier work on this subject (Whitham 1952), only problems having directional symmetry were considered; thus, steady supersonic flow past an axisymmetrical body was a typical example. The present paper extends the method to problems lacking such symmetry. The main step required in the extension is described in the introduction and the general theory is completed in §2; the remainder of the paper is devoted to applications of the theory in specific cases. First, in §3, the problem of the outward propagation of spherical shocks is reconsidered since it provides the simplest illustration of the ideas developed in §2. Then, in §4, the theory is applied to a model of an unsymmetrical explosion. In §5, a brief outline is given of the theory developed by Rao (1956) for the application to a supersonic projectile moving with varying speed and direction. Examples of steady supersonic flow past unsymmetrical bodies are discussed in §6 and 7. The first is the flow past a flat plate delta wing at small incidence to the stream, with leading edges swept inside the Mach cone; the results agree with those previously found by Lighthill (1949) in his work on shocks in cone field problems, and this provides a valuable check on the theory. The second application in steady supersonic flow is to the problem of a thin wing having a finite curved leading edge. It is found that in any given direction the shock from the leading edge ultimately decays exactly as for the bow shock on a body of revolution; the equivalent body of revolution for any direction is determined in terms of the thickness distribution of the wing and varies with the direction chosen. Finally in §8, the wave drag on the wing is calculated from the rate of dissipation of energy by the shocks. The drag is found to be the mean of the drags on the equivalent bodies of revolution for the different directions. © 1956, Cambridge University Press. All rights reserved.},\n\tnumber = {3},\n\tjournal = {Journal of Fluid Mechanics},\n\tauthor = {Whitham, G. B.},\n\tyear = {1956},\n\tnote = {Publisher: Cambridge University Press},\n\tpages = {290--318},\n}\n\n\n\n
\n
\n\n\n
\n A method is presented for treating problems of the propagation and ultimate decay of the shocks produced by explosions and by bodies in supersonic flight. The theory is restricted to weak shocks, but is of quite general application within that limitation. In the author's earlier work on this subject (Whitham 1952), only problems having directional symmetry were considered; thus, steady supersonic flow past an axisymmetrical body was a typical example. The present paper extends the method to problems lacking such symmetry. The main step required in the extension is described in the introduction and the general theory is completed in §2; the remainder of the paper is devoted to applications of the theory in specific cases. First, in §3, the problem of the outward propagation of spherical shocks is reconsidered since it provides the simplest illustration of the ideas developed in §2. Then, in §4, the theory is applied to a model of an unsymmetrical explosion. In §5, a brief outline is given of the theory developed by Rao (1956) for the application to a supersonic projectile moving with varying speed and direction. Examples of steady supersonic flow past unsymmetrical bodies are discussed in §6 and 7. The first is the flow past a flat plate delta wing at small incidence to the stream, with leading edges swept inside the Mach cone; the results agree with those previously found by Lighthill (1949) in his work on shocks in cone field problems, and this provides a valuable check on the theory. The second application in steady supersonic flow is to the problem of a thin wing having a finite curved leading edge. It is found that in any given direction the shock from the leading edge ultimately decays exactly as for the bow shock on a body of revolution; the equivalent body of revolution for any direction is determined in terms of the thickness distribution of the wing and varies with the direction chosen. Finally in §8, the wave drag on the wing is calculated from the rate of dissipation of energy by the shocks. The drag is found to be the mean of the drags on the equivalent bodies of revolution for the different directions. © 1956, Cambridge University Press. All rights reserved.\n
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\n  \n 1955\n \n \n (2)\n \n \n
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\n \n \n
\n \n\n \n \n Mirels, H.\n\n\n \n \n \n \n Laminar Boundary Layer Behind Shock Advancing into Stationary Fluid.\n \n \n \n\n\n \n\n\n\n Technical Report 3401, National Advisory Committee for Aeronautics, 1955.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@techreport{mirels1955,\n\ttitle = {Laminar {Boundary} {Layer} {Behind} {Shock} {Advancing} into {Stationary} {Fluid}},\n\tnumber = {3401},\n\tinstitution = {National Advisory Committee for Aeronautics},\n\tauthor = {Mirels, Harold},\n\tyear = {1955},\n}\n\n\n\n
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\n \n\n \n \n Bisplinghoff, R.; Ashley, H.; and Halfman, R.\n\n\n \n \n \n \n Aeroelasticity.\n \n \n \n\n\n \n\n\n\n Addison-Wesley, Cambridge, 1955.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@book{bisplinghoff1955,\n\taddress = {Cambridge},\n\ttitle = {Aeroelasticity},\n\tpublisher = {Addison-Wesley},\n\tauthor = {Bisplinghoff, R. and Ashley, H. and Halfman, R.},\n\tyear = {1955},\n}\n\n\n\n
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\n  \n 1954\n \n \n (1)\n \n \n
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\n \n\n \n \n Bhatnagar, P. L.; Gross, E. P.; and Krook, M.\n\n\n \n \n \n \n A Model for Collision Processes in Gases. I. Small Amplitude Processes in Charged and Neutral One-Component Systems.\n \n \n \n\n\n \n\n\n\n Physical Review, 94(3). May 1954.\n Publisher: American Physical Society\n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
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@article{bhatnagar1954,\n\ttitle = {A {Model} for {Collision} {Processes} in {Gases}. {I}. {Small} {Amplitude} {Processes} in {Charged} and {Neutral} {One}-{Component} {Systems}},\n\tvolume = {94},\n\tdoi = {10.1103/PhysRev.94.511},\n\tabstract = {A kinetic theory approach to collision processes in ionized and neutral gases is presented. This approach is adequate for the unified treatment of the dynamic properties of gases over a continuous range of pressures from the Knudsen limit to the high-pressure limit where the aerodynamic equations are valid. It is also possible to satisfy the correct microscopic boundary conditions. The method consists in altering the collision terms in the Boltzmann equation. The modified collision terms are constructed so that each collision conserves particle number, momentum, and energy; other characteristics such as persistence of velocities and angular dependence may be included. The present article illustrates the technique for a simple model involving the assumption of a collision time independent of velocity; this model is applied to the study of small amplitude oscillations of one-component ionized and neutral gases. The initial value problem for unbounded space is solved by performing a Fourier transformation on the space variables and a Laplace transformation on the time variable. For uncharged gases there results the correct adiabatic limiting law for sound-wave propagation at high pressures and, in addition, one obtains a theory of absorption and dispersion of sound for arbitrary pressures. For ionized gases the difference in the nature of the organization in the low-pressure plasma oscillations and in high-pressure sound-type oscillations is studied. Two important cases are distinguished. If the wavelengths of the oscillations are long compared to either the Debye length or the mean free path, a small change in frequency is obtained as the collision frequency varies from zero to infinity. The accompanying absorption is small; it reaches its maximum value when the collision frequency equals the plasma frequency. The second case refers to waves shorter than both the Debye length and the mean free path; these waves are characterized by a very heavy absorption. © 1954 The American Physical Society.},\n\tnumber = {3},\n\tjournal = {Physical Review},\n\tauthor = {Bhatnagar, P. L. and Gross, E. P. and Krook, M.},\n\tmonth = may,\n\tyear = {1954},\n\tnote = {Publisher: American Physical Society},\n}\n\n\n\n
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\n A kinetic theory approach to collision processes in ionized and neutral gases is presented. This approach is adequate for the unified treatment of the dynamic properties of gases over a continuous range of pressures from the Knudsen limit to the high-pressure limit where the aerodynamic equations are valid. It is also possible to satisfy the correct microscopic boundary conditions. The method consists in altering the collision terms in the Boltzmann equation. The modified collision terms are constructed so that each collision conserves particle number, momentum, and energy; other characteristics such as persistence of velocities and angular dependence may be included. The present article illustrates the technique for a simple model involving the assumption of a collision time independent of velocity; this model is applied to the study of small amplitude oscillations of one-component ionized and neutral gases. The initial value problem for unbounded space is solved by performing a Fourier transformation on the space variables and a Laplace transformation on the time variable. For uncharged gases there results the correct adiabatic limiting law for sound-wave propagation at high pressures and, in addition, one obtains a theory of absorption and dispersion of sound for arbitrary pressures. For ionized gases the difference in the nature of the organization in the low-pressure plasma oscillations and in high-pressure sound-type oscillations is studied. Two important cases are distinguished. If the wavelengths of the oscillations are long compared to either the Debye length or the mean free path, a small change in frequency is obtained as the collision frequency varies from zero to infinity. The accompanying absorption is small; it reaches its maximum value when the collision frequency equals the plasma frequency. The second case refers to waves shorter than both the Debye length and the mean free path; these waves are characterized by a very heavy absorption. © 1954 The American Physical Society.\n
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\n  \n 1950\n \n \n (2)\n \n \n
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\n \n\n \n \n Wilke, C. R.\n\n\n \n \n \n \n \n A Viscosity Equation for Gas Mixtures.\n \n \n \n \n\n\n \n\n\n\n The Journal of Chemical Physics, 18(4): 517–519. April 1950.\n _eprint: https://pubs.aip.org/aip/jcp/article-pdf/18/4/517/18796913/517_1_online.pdf\n\n\n\n
\n\n\n\n \n \n \"APaper\n  \n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n  \n \n abstract \n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{wilke_viscosity_1950,\n\ttitle = {A {Viscosity} {Equation} for {Gas} {Mixtures}},\n\tvolume = {18},\n\tissn = {0021-9606},\n\turl = {https://doi.org/10.1063/1.1747673},\n\tdoi = {10.1063/1.1747673},\n\tabstract = {By application of the kinetic theory, with several simplifying assumptions, the previous equation of Buddenberg and the author has been modified to give a general equation for viscosity as a function of molecular weights and viscosities of the pure components of the mixture. Agreement of the equation with experimental data is demonstrated for a number of highly irregular binary gas systems and mixtures of three to seven components.},\n\tnumber = {4},\n\tjournal = {The Journal of Chemical Physics},\n\tauthor = {Wilke, C. R.},\n\tmonth = apr,\n\tyear = {1950},\n\tnote = {\\_eprint: https://pubs.aip.org/aip/jcp/article-pdf/18/4/517/18796913/517\\_1\\_online.pdf},\n\tpages = {517--519},\n}\n\n\n\n
\n
\n\n\n
\n By application of the kinetic theory, with several simplifying assumptions, the previous equation of Buddenberg and the author has been modified to give a general equation for viscosity as a function of molecular weights and viscosities of the pure components of the mixture. Agreement of the equation with experimental data is demonstrated for a number of highly irregular binary gas systems and mixtures of three to seven components.\n
\n\n\n
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\n \n\n \n \n Wilke, C R\n\n\n \n \n \n \n A Viscosity Equation for Gas Mixtures.\n \n \n \n\n\n \n\n\n\n The Journal of Chemical Physics, 18(4): 517–519. 1950.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{wilke1950,\n\ttitle = {A {Viscosity} {Equation} for {Gas} {Mixtures}},\n\tvolume = {18},\n\tdoi = {10.1063/1.1747673},\n\tnumber = {4},\n\tjournal = {The Journal of Chemical Physics},\n\tauthor = {Wilke, C R},\n\tyear = {1950},\n\tpages = {517--519},\n}\n\n\n\n
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\n  \n 1949\n \n \n (2)\n \n \n
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\n \n\n \n \n Herring, C.; and Nichols, M. H.\n\n\n \n \n \n \n Thermionic Emission.\n \n \n \n\n\n \n\n\n\n Reviews of Modern Physics, 21(2). 1949.\n Publisher: American Physical Society\n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{herring1949,\n\ttitle = {Thermionic {Emission}},\n\tvolume = {21},\n\tdoi = {10.1103/RevModPhys.21.185},\n\tnumber = {2},\n\tjournal = {Reviews of Modern Physics},\n\tauthor = {Herring, Conyers and Nichols, M. H.},\n\tyear = {1949},\n\tnote = {Publisher: American Physical Society},\n}\n\n\n\n
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\n \n\n \n \n Bohm, D\n\n\n \n \n \n \n The Characteristics of Electrical Discharges in Magnetic Fields.\n \n \n \n\n\n \n\n\n\n In Guthrie, A, editor(s). McGraw-Hill, 1949.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@incollection{bohm1949,\n\ttitle = {The {Characteristics} of {Electrical} {Discharges} in {Magnetic} {Fields}},\n\tpublisher = {McGraw-Hill},\n\tauthor = {Bohm, D},\n\teditor = {Guthrie, A},\n\tyear = {1949},\n}\n\n\n\n
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\n  \n 1940\n \n \n (1)\n \n \n
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\n \n\n \n \n Bethe, H. A.; and Teller, E.\n\n\n \n \n \n \n Deviations from thermal equilibrium in shock waves.\n \n \n \n\n\n \n\n\n\n University Microfilms, Incorporated, 1940.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@book{bethe1940,\n\ttitle = {Deviations from thermal equilibrium in shock waves},\n\tpublisher = {University Microfilms, Incorporated},\n\tauthor = {Bethe, Hans Albrecht and Teller, Edward},\n\tyear = {1940},\n}\n\n\n\n
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\n  \n 1932\n \n \n (1)\n \n \n
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\n \n\n \n \n Dunham, J L\n\n\n \n \n \n \n The Energy Levels of a Rotating Vibrator.\n \n \n \n\n\n \n\n\n\n Physical Review, 41(6): 721–731. 1932.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{dunham1932,\n\ttitle = {The {Energy} {Levels} of a {Rotating} {Vibrator}},\n\tvolume = {41},\n\tdoi = {10.1103/PhysRev.41.721},\n\tnumber = {6},\n\tjournal = {Physical Review},\n\tauthor = {Dunham, J L},\n\tyear = {1932},\n\tpages = {721--731},\n}\n\n\n\n
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\n  \n 1930\n \n \n (1)\n \n \n
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\n \n\n \n \n Dushman, S.\n\n\n \n \n \n \n Thermionic Emission.\n \n \n \n\n\n \n\n\n\n Reviews of Modern Physics, 2(4). 1930.\n Publisher: American Physical Society\n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{dushman1930,\n\ttitle = {Thermionic {Emission}},\n\tvolume = {2},\n\tdoi = {10.1103/RevModPhys.2.381},\n\tnumber = {4},\n\tjournal = {Reviews of Modern Physics},\n\tauthor = {Dushman, Saul},\n\tyear = {1930},\n\tnote = {Publisher: American Physical Society},\n}\n\n\n\n
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\n  \n 1921\n \n \n (1)\n \n \n
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\n \n\n \n \n Richardson, O W\n\n\n \n \n \n \n Emission of Electricty from Hot Bodies.\n \n \n \n\n\n \n\n\n\n Longmans, Green, and Co., 1921.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@book{richardson1921,\n\ttitle = {Emission of {Electricty} from {Hot} {Bodies}},\n\tpublisher = {Longmans, Green, and Co.},\n\tauthor = {Richardson, O W},\n\tyear = {1921},\n}\n\n\n\n
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\n  \n 1915\n \n \n (1)\n \n \n
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\n \n\n \n \n Howell, J. T.\n\n\n \n \n \n \n The Index of Refraction of Gases.\n \n \n \n\n\n \n\n\n\n Physical Review, 6(2): 81–93. August 1915.\n \n\n\n\n
\n\n\n\n \n\n \n \n doi\n  \n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{howell1915,\n\ttitle = {The {Index} of {Refraction} of {Gases}},\n\tvolume = {6},\n\tissn = {0031-899X},\n\tdoi = {10.1103/PhysRev.6.81},\n\tlanguage = {en},\n\tnumber = {2},\n\turldate = {2023-01-27},\n\tjournal = {Physical Review},\n\tauthor = {Howell, Janet Tucker},\n\tmonth = aug,\n\tyear = {1915},\n\tpages = {81--93},\n}\n\n\n\n
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\n  \n 1903\n \n \n (2)\n \n \n
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\n \n\n \n \n Richardson, O W\n\n\n \n \n \n \n The Electrical Conductivity Imparted to a Vacuum by Hot Conductors.\n \n \n \n\n\n \n\n\n\n Philosophical Transactions of the Royal Society of London, 201: 497–549. 1903.\n \n\n\n\n
\n\n\n\n \n\n \n\n \n link\n  \n \n\n bibtex\n \n\n \n\n \n\n \n \n \n \n \n \n \n\n  \n \n \n\n\n\n
\n 
@article{richardson1903a,\n\ttitle = {The {Electrical} {Conductivity} {Imparted} to a {Vacuum} by {Hot} {Conductors}},\n\tvolume = {201},\n\tjournal = {Philosophical Transactions of the Royal Society of London},\n\tauthor = {Richardson, O W},\n\tyear = {1903},\n\tpages = {497--549},\n}\n\n\n\n
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\n \n\n \n \n Richardson, O W\n\n\n \n \n \n \n On the negative radiation form hot platinum.\n \n \n \n\n\n \n\n\n\n Philosophical of the Cambridge Philosophical Society. 1903.\n \n\n\n\n
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\n 
@article{richardson1903,\n\ttitle = {On the negative radiation form hot platinum},\n\tjournal = {Philosophical of the Cambridge Philosophical Society},\n\tauthor = {Richardson, O W},\n\tyear = {1903},\n}\n\n\n\n
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\n  \n\n  \n  \n  Department of Commerce, U.\n\n\n  \n  \n  \n  \n  \n    National Institute of Standards and Technology.\n  \n  \n  \n  \n\n\n  \n\n\n\n   \n  \n\n\n\n
\n\n\n\n  \n  \n    \"NationalPaper\n   \n  \n\n  \n\n  \n  link\n   \n  \n\n  bibtex\n    \n\n  \n\n  \n\n  \n  \n  \n  \n  \n  \n  \n\n   \n  \n  \n\n\n\n
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@misc{department_of_commerce_national_nodate,\n\ttitle = {National {Institute} of {Standards} and {Technology}},\n\turl = {https://webbook.nist.gov/chemistry/},\n\tjournal = {National Institute of Standards and Technology},\n\tauthor = {Department of Commerce, USA},\n}\n\n\n\n
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\n  \n\n  \n  \n  \n\n\n  \n  \n  \n  \n  \n    NASA's Space Launch System Reference Guide.\n  \n  \n  \n  \n\n\n  \n\n\n\n   \n  \n\n\n\n
\n\n\n\n  \n  \n    \"NASA'sPaper\n   \n  \n\n  \n\n  \n  link\n   \n  \n\n  bibtex\n    \n\n  \n\n  \n\n  \n  \n  \n  \n  \n  \n  \n\n   \n  \n  \n\n\n\n
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@misc{slsreference,\n\ttitle = {{NASA}'s {Space} {Launch} {System} {Reference} {Guide}},\n\turl = {https://www.nasa.gov/wp-content/uploads/2021/12/sls_reference_guide_2022_print_0.pdf?emrc=c4647a},\n}\n\n\n\n
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\n  \n\n  \n  \n  Carter, B.\n\n\n  \n  \n  \n  \n  \n    Episode 36: The Hypersonic Materialist.\n  \n  \n  \n  \n\n\n  \n\n\n\n   \n  Date: 2020\n\n\n\n
\n\n\n\n  \n  \n    \"EpisodePaper\n   \n  \n\n  \n\n  \n  link\n   \n  \n\n  bibtex\n    \n\n  \n\n  \n\n  \n  \n  \n  \n  \n  \n  \n\n   \n  \n  \n\n\n\n
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@misc{carter2020,\n\ttitle = {Episode 36: {The} {Hypersonic} {Materialist}},\n\turl = {https://www.darpa.mil/news-events/2020-12-01a},\n\turldate = {2024-04-30},\n\tauthor = {Carter, Bill},\n\tnote = {Date: 2020},\n}\n\n\n\n
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\n  \n\n  \n  \n  Hoy, J. F.;  and Bermejo-Moreno, I.\n\n\n  \n  \n  \n  \n  Numerical study of STBLI on flexible panels with wall-modeled LES.\n  \n  \n  \n\n\n  \n\n\n\n  In AIAA Scitech 2021 Forum,  . AIAA Paper 2021-0250\n  \n\n\n\n
\n\n\n\n  \n\n  \n\n  \n  link\n   \n  \n\n  bibtex\n    \n\n  \n   \n  \n    abstract \n  \n\n  \n\n  \n  \n  \n  \n  \n  \n  \n\n   \n  \n  \n\n\n\n
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@inproceedings{hoy,\n\ttitle = {Numerical study of {STBLI} on flexible panels with wall-modeled {LES}},\n\tabstract = {View Video Presentation: https://doi.org/10.2514/6.2021-0250.vidCoupled fluid structure interaction (FSI) simulations with wall-modeled LES (WMLES) are used to capture the interaction of an oblique shock impinging on the turbulent boundary layer developed along a flexible panel. The simulations replicate prior experiments conducted at the trisonic wind tunnel (TMK) of the Supersonic and Hypersonic Technologies Department at DLR, Cologne. The flow has a freestream Mach number of 3, and an incoming turbulent boundary layer thickness of 4 mm upstream of the interaction. It is impinged by an oblique shock generated by a rotating wedge with a maximum deflection angle of 17.5 degrees, reached approximately 15 milliseconds after starting from a zero wedge angle corresponding to a shock-free panel. Displacement signals over time at different panel locations are compared to the experiments and to a previous FSI numerical wall-resolved large-eddy simulation. The effect of flexibility on the wall pressure as a function of streamwise location and time is assessed, showing a modulation by the panel vibration that affects the full panel streamwise extent. Wall pressure power spectral densities show an elongation of the frequency band associated with flow separation region for the flexible case over the nominal rigid configuration. Additionally, the turbulent boundary layer of the flexible panel takes a longer distance to recover downstream of the oblique shock. The peak contribution of the low frequency motions to the power spectrum is increased for the flexible case. The study of separation bubble dynamics reveals that panel flexibility increases the separation length and volume, but leaves the bubble streamwise centroid nearly unaffected.},\n\turldate = {2023-08-11},\n\tbooktitle = {{AIAA} {Scitech} 2021 {Forum}},\n\tpublisher = {AIAA Paper 2021-0250},\n\tauthor = {Hoy, Jonathan F. and Bermejo-Moreno, Ivan},\n}\n\n\n\n\n\n\n\n\n\n\n\n
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\n  View Video Presentation: https://doi.org/10.2514/6.2021-0250.vidCoupled fluid structure interaction (FSI) simulations with wall-modeled LES (WMLES) are used to capture the interaction of an oblique shock impinging on the turbulent boundary layer developed along a flexible panel. The simulations replicate prior experiments conducted at the trisonic wind tunnel (TMK) of the Supersonic and Hypersonic Technologies Department at DLR, Cologne. The flow has a freestream Mach number of 3, and an incoming turbulent boundary layer thickness of 4 mm upstream of the interaction. It is impinged by an oblique shock generated by a rotating wedge with a maximum deflection angle of 17.5 degrees, reached approximately 15 milliseconds after starting from a zero wedge angle corresponding to a shock-free panel. Displacement signals over time at different panel locations are compared to the experiments and to a previous FSI numerical wall-resolved large-eddy simulation. The effect of flexibility on the wall pressure as a function of streamwise location and time is assessed, showing a modulation by the panel vibration that affects the full panel streamwise extent. Wall pressure power spectral densities show an elongation of the frequency band associated with flow separation region for the flexible case over the nominal rigid configuration. Additionally, the turbulent boundary layer of the flexible panel takes a longer distance to recover downstream of the oblique shock. The peak contribution of the low frequency motions to the power spectrum is increased for the flexible case. The study of separation bubble dynamics reveals that panel flexibility increases the separation length and volume, but leaves the bubble streamwise centroid nearly unaffected.\n
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\n  \n\n  \n  \n  \n\n\n  \n  \n  \n  \n  \n    United States - SEDS - U.S. Energy Information Administration (EIA).\n  \n  \n  \n  \n\n\n  \n\n\n\n  .  .\n  \n\n\n\n
\n\n\n\n  \n  \n    \"UnitedPaper\n   \n  \n\n  \n\n  \n  link\n   \n  \n\n  bibtex\n    \n\n  \n\n  \n\n  \n  \n  \n  \n  \n  \n  \n\n   \n  \n  \n\n\n\n
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@article{zotero-1234,\n\ttitle = {United {States} - {SEDS} - {U}.{S}. {Energy} {Information} {Administration} ({EIA})},\n\turl = {https://www.eia.gov/state/seds/data.php?incfile=/state/seds/sep_fuel/html/fuel_jf.html},\n}\n\n\n\n
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\n  \n\n  \n  \n  Schuler, C. J.; Ward, L. K.;  and Hodapp, A.\n\n\n  \n  \n  \n  \n  \n    Techniques for Measurement of Dynamic Stability Derivatives in Ground Test Facilities.\n  \n  \n  \n  \n\n\n  \n\n\n\n  Technical Report  .\n  \n\n\n\n
\n\n\n\n  \n  \n    \"TechniquesPaper\n   \n  \n\n  \n\n  \n  link\n   \n  \n\n  bibtex\n    \n\n  \n\n  \n\n  \n  \n  \n  \n  \n  \n  \n\n   \n  \n  \n\n\n\n
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@techreport{schuler,\n\ttitle = {Techniques for {Measurement} of {Dynamic} {Stability} {Derivatives} in {Ground} {Test} {Facilities}},\n\turl = {http://www.dtic.mil/docs/citations/ AD0669227.},\n\tauthor = {Schuler, C. J. and Ward, L. K. and Hodapp, A.},\n}\n\n\n\n
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\n  \n\n  \n  \n  Gupta, A.;  and Argrow, B.\n\n\n  \n  \n  \n  \n  Analytical Approach for Aero-Optical & Atmospheric Effects in Supersonic Flow Fields.\n  \n  \n  \n\n\n  \n\n\n\n  Technical Report  .\n  \n\n\n\n
\n\n\n\n  \n\n  \n\n  \n  link\n   \n  \n\n  bibtex\n    \n\n  \n   \n  \n    abstract \n  \n\n  \n\n  \n  \n  \n  \n  \n  \n  \n\n   \n  \n  \n\n\n\n
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@techreport{gupta,\n\ttitle = {Analytical {Approach} for {Aero}-{Optical} \\& {Atmospheric} {Effects} in {Supersonic} {Flow} {Fields}},\n\tabstract = {Radio blackout is commonly associated with interference from plasma created around high-speed aerospace and re-entry vehicles. Alternative communication means, including lasers at optical frequencies, has emerged as promising counter to the problem. The refractive index of a medium, such as air, governs the angular shift in the path of an optical signal. For a fluid, the refractive index is a function of the thermodynamic state. Drastic changes in the thermodynamic variables across the shock wave changes the downstream refractive index. This paper presents an investigation of how changes to the thermodynamic state of air for high-speed flow (not including chemical reactions) affects optical propagation. Analytical expressions for horizontal deviation and angular shifts induced by-shock layer, shock wave and atmosphere, are derived for an optical signal that travels from a high-speed vehicle to the ground. The formulation has been verified computationally for the supersonic flow about a wedge and cone that capture effects from flow gradients. I. Nomenclature α = communication angle [deg] α * = inflex communication angle [deg] β = shock angle [deg] ˆ θ = estimated angle to ground [deg] θ c = semi-vertex angle of the body [deg] θ d m = approach angle to shock [deg] θ u0 = refraction angle after shock [deg] θ u n = approach angle to ground [deg] ∆θ = small angular difference between consecutive rays in shock layer [deg] κ = Gladstone-Dale constant [m 3 /kg] ˆ φ = estimated approach angle to shock wave [deg] φ * d m = inflex approach angle [deg] φ * u0 = inflex refraction angle in upstream [deg] φ di = incident angle at the interface of i th and (i + 1) th sub-layer of shock layer [deg] φ dir = refraction angle at the interface of i th and (i + 1) th sub-layer of shock layer [deg] φ u0 = refraction angle in upstream [deg] ω = angular shift [deg] ω = augmented angular shift [deg] n d m = downstream refractive index of m th sub-layer of shock layer n u0 = upstream refractive index at the cruising altitude n u n = upstream refractive index of n th atmospheric layer x = actual horizontal distance on surface [m] ˆ x = estimated horizontal distance on surface [m] x u = actual horizontal distance before reaching first atmospheric layer [m] x r i = actual horizontal distance in i th atmospheric layer [m]},\n\tauthor = {Gupta, Anubhav and Argrow, Brian},\n}\n\n\n\n
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\n  Radio blackout is commonly associated with interference from plasma created around high-speed aerospace and re-entry vehicles. Alternative communication means, including lasers at optical frequencies, has emerged as promising counter to the problem. The refractive index of a medium, such as air, governs the angular shift in the path of an optical signal. For a fluid, the refractive index is a function of the thermodynamic state. Drastic changes in the thermodynamic variables across the shock wave changes the downstream refractive index. This paper presents an investigation of how changes to the thermodynamic state of air for high-speed flow (not including chemical reactions) affects optical propagation. Analytical expressions for horizontal deviation and angular shifts induced by-shock layer, shock wave and atmosphere, are derived for an optical signal that travels from a high-speed vehicle to the ground. The formulation has been verified computationally for the supersonic flow about a wedge and cone that capture effects from flow gradients. I. Nomenclature α = communication angle [deg] α * = inflex communication angle [deg] β = shock angle [deg] ˆ θ = estimated angle to ground [deg] θ c = semi-vertex angle of the body [deg] θ d m = approach angle to shock [deg] θ u0 = refraction angle after shock [deg] θ u n = approach angle to ground [deg] ∆θ = small angular difference between consecutive rays in shock layer [deg] κ = Gladstone-Dale constant [m 3 /kg] ˆ φ = estimated approach angle to shock wave [deg] φ * d m = inflex approach angle [deg] φ * u0 = inflex refraction angle in upstream [deg] φ di = incident angle at the interface of i th and (i + 1) th sub-layer of shock layer [deg] φ dir = refraction angle at the interface of i th and (i + 1) th sub-layer of shock layer [deg] φ u0 = refraction angle in upstream [deg] ω = angular shift [deg] ω = augmented angular shift [deg] n d m = downstream refractive index of m th sub-layer of shock layer n u0 = upstream refractive index at the cruising altitude n u n = upstream refractive index of n th atmospheric layer x = actual horizontal distance on surface [m] ˆ x = estimated horizontal distance on surface [m] x u = actual horizontal distance before reaching first atmospheric layer [m] x r i = actual horizontal distance in i th atmospheric layer [m]\n
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