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\n \n 2029\n \n \n (1)\n \n \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 2029.\n \n\n\n\n
\n\n\n\n \n \n $\"United$ Website\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{\n title = {United States - SEDS - U.S. Energy Information Administration (EIA)},\n type = {misc},\n year = {2029},\n source = {U.S. Energy Information Administration},\n websites = {https://www.eia.gov/state/seds/data.php?incfile=/state/seds/sep_fuel/html/fuel_jf.html},\n id = {bc3e78d5-8d68-31b7-8c3c-65a55e22768c},\n created = {2021-04-21T21:19:57.224Z},\n accessed = {2021-04-21},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-07-23T21:07:16.602Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {eai:2019},\n private_publication = {false},\n bibtype = {misc},\n author = {}\n}

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\n \n 2023\n \n \n (1)\n \n \n

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\n \n\n \n \n Hanquist, K., M.; Tumuklu, O.; and Larsen, A.\n\n\n \n \n \n \n State-to-State and Shock-tube Thermochemical Modeling of Hypersonic Flows.\n \n \n \n\n\n \n\n\n\n In AIAA AVIATION, 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

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@inproceedings{\n title = {State-to-State and Shock-tube Thermochemical Modeling of Hypersonic Flows},\n type = {inproceedings},\n year = {2023},\n id = {c3d13af6-0663-3928-b313-654a05147263},\n created = {2022-11-14T20:29:24.260Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2023-05-02T04:44:07.568Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {hanquist:aviation:23},\n private_publication = {false},\n bibtype = {inproceedings},\n author = {Hanquist, Kyle M. and Tumuklu, Ozgur and Larsen, Aaron},\n booktitle = {AIAA AVIATION}\n}

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\n \n 2022\n \n \n (11)\n \n \n

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\n \n\n \n \n Needels, J., T.; Duzel, U.; Hanquist, K., M.; and Alonso, J., J.\n\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\n In AIAA SCITECH 2022 Forum, 2022. AIAA Paper 2022-1636\n \n\n\n\n
\n\n\n\n \n \n $\"Sensitivity$ 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

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@inproceedings{\n title = {Sensitivity Analysis of Gas-Surface Modeling in Nonequilibrium Flows},\n type = {inproceedings},\n year = {2022},\n publisher = {AIAA Paper 2022-1636},\n id = {35e7f4b4-8d28-3104-8dd6-82f26fe9b8c8},\n created = {2022-01-18T03:24:11.584Z},\n accessed = {2022-01-17},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-01-18T03:24:12.275Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {needels:scitech:2022},\n private_publication = {false},\n abstract = {In this paper, the SU2-NEMO CFD solver is used to simulate conditions in the HyMETS arc jet test facility in order to test models of gas-surface interaction for catalytic heating augmentation in nonequilibrium flows. Simulation predictions of surface heat flux and pressure on a calorimeter probe are verified and validated against numerical results and experimental data. A sensitivity analysis with respect to surface chemistry modeling parameters is then conducted focusing on the impact of catalytic efficiency on surface heating rates. Nomenclature í µí± = total energy per unit mass í µí± í µí±£í µí± = vibrational-electronic energy per unit mass F í µí± = convective flux F í µí±£ = viscous flux ℎ = total enthalpy per unit mass I = identity matrix J = diffusion velocity vector í µí± í µí± = number of species n = wall normal unit vector í µí± = pressure Q = source term vector R = residual vector U = conservative state vector u = velocity vector q = thermal conduction í µí± = heat flux magnitude í µí± = mass fraction í µí»¾ = catalytic efficiency Θ í µí±¡í µí±:í µí±£í µí± = energy exchange source term í µí¼ = density í µí½ = viscous stress tensor í µí¼ = chemical volumetric production rate Subscripts í µí± = chemical species index í µí±¤ = wall quantity Superscripts í µí±í µí±í µí±¡ = catalytic í µí±í µí±í µí± = incident í µí± = energy mode index í µí±í µí±í µí± = recombining í µí±¡í µí± = translational-rotational energy mode í µí±£í µí± = vibrational-electronic energy mode},\n bibtype = {inproceedings},\n author = {Needels, Jacob T. and Duzel, Umran and Hanquist, Kyle M. and Alonso, Juan J.},\n doi = {10.2514/6.2022-1636},\n booktitle = {AIAA SCITECH 2022 Forum}\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 \n\n\n\n
\n\n\n\n \n \n $\"Hypersonic$ Website\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{\n title = {Hypersonic Challenges},\n type = {misc},\n year = {2022},\n websites = {https://www.aiaa.org/events-learning/event/2022/04/28/default-calendar/aiaa-webinar-hypersonics-challenges},\n publisher = {AIAA},\n id = {fac69895-bdfa-39db-85a2-1cbabe4ac9c1},\n created = {2022-05-31T18:31:19.127Z},\n accessed = {2022-05-31},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-05-31T18:31:19.127Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {chazot:aiaa},\n source_type = {Webinar},\n private_publication = {false},\n bibtype = {misc},\n author = {Chazot, O.}\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 \n Kinetic and Continuum Modeling of High-Temperature Air Relaxation.\n \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 $\"Kinetic$ Paper\n \n \n \n $\"Kinetic$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\n \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{\n title = {Kinetic and Continuum Modeling of High-Temperature Air Relaxation},\n type = {article},\n year = {2022},\n keywords = {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},\n pages = {1-23},\n websites = {https://arc.aiaa.org/doi/full/10.2514/1.T6462},\n publisher = {American Institute of Aeronautics and Astronautics},\n id = {605c7d02-2967-34ca-9fb8-6ee80ecbfac3},\n created = {2022-06-04T15:31:37.621Z},\n accessed = {2022-06-04},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-06-04T15:32:35.199Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {gimelshein:jtht:2022},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {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 doi = {10.2514/1.T6462},\n journal = {Journal of Thermophysics and Heat Transfer}\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 \n Multiscale Modeling of Gas–Solid Surface Interactions Under High-Temperature Gas Effect.\n \n \n \n \n\n\n \n\n\n\n Journal of Thermophysics and Heat Transfer,1-13. 6 2022.\n \n\n\n\n
\n\n\n\n \n \n $\"Multiscale$ 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\n \n \n \n \n \n \n \n\n \n \n \n\n\n\n

\n

@article{\n title = {Multiscale Modeling of Gas–Solid Surface Interactions Under High-Temperature Gas Effect},\n type = {article},\n year = {2022},\n pages = {1-13},\n month = {6},\n day = {3},\n id = {ef3399ab-3506-3d87-9767-b770dea4510c},\n created = {2022-06-07T16:10:22.309Z},\n accessed = {2022-06-07},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-06-07T16:10:23.019Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {qui:jtht:2022},\n private_publication = {false},\n bibtype = {article},\n author = {Qiu, Tianhao and Zhao, Mingcan and Li, Yanping and Li, Chengxiang and Ge, Wei},\n doi = {10.2514/1.T6456},\n journal = {Journal of Thermophysics and Heat Transfer}\n}

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\n \n\n \n \n Viladegut, A.; and Chazot, O.\n\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\n Physics of Fluids, 34(2): 027108. 2 2022.\n \n\n\n\n
\n\n\n\n \n \n $\"Catalytic$ Paper\n \n \n \n $\"Catalytic$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\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{\n title = {Catalytic characterization in plasma wind tunnels under the influence of gaseous recombination},\n type = {article},\n year = {2022},\n pages = {027108},\n volume = {34},\n websites = {https://aip.scitation.org/doi/abs/10.1063/5.0077603},\n month = {2},\n publisher = {AIP Publishing LLCAIP Publishing},\n day = {7},\n id = {c1fcc518-e66d-3b5e-a466-92b4ea1053c0},\n created = {2022-06-08T14:05:42.609Z},\n accessed = {2022-06-08},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-06-08T14:05:46.446Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {viladegut:pf:2022},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Viladegut, A. and Chazot, O.},\n doi = {10.1063/5.0077603},\n journal = {Physics of Fluids},\n number = {2}\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 AIAA Journal, 60(1): 31-40. 8 2022.\n \n\n\n\n
\n\n\n\n \n \n $\"Influence$ Paper\n \n \n \n $\"Influence$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\n \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{\n title = {Influence of Chemical Kinetics Models on Plasma Generation in Hypersonic Flight},\n type = {article},\n year = {2022},\n keywords = {Angle of Attack,Bow Shock,CFD Analysis,Chemical Kinetics,Flight Data,Flight Testing,Free Molecular Flow,Hypersonic Flight,No Slip Condition,Plasma Diagnostics},\n pages = {31-40},\n volume = {60},\n websites = {https://arc.aiaa.org/doi/10.2514/1.J060615},\n month = {8},\n publisher = {AIAA International},\n day = {23},\n id = {75b180cb-8afd-36b6-aa29-6d1b7c70ea8b},\n created = {2022-06-08T18:21:27.568Z},\n accessed = {2022-06-08},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-06-08T18:21:28.284Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {sawick:aj:2021},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Sawicki, Pawel and Chaudhry, Ross S. and Boyd, Iain D.},\n doi = {10.2514/1.J060615/ASSET/IMAGES/LARGE/FIGURE11.JPEG},\n journal = {AIAA Journal},\n number = {1}\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 AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2022, 2022. American Institute of Aeronautics and Astronautics Inc, AIAA\n \n\n\n\n
\n\n\n\n \n \n $\"Development$ Paper\n \n \n \n $\"Development$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\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{\n title = {Development and Validation Studies of a Multi-purpose DSMC Code},\n type = {inproceedings},\n year = {2022},\n websites = {https://arc.aiaa.org/doi/10.2514/6.2022-2017},\n publisher = {American Institute of Aeronautics and Astronautics Inc, AIAA},\n id = {b92bc4e7-4a4c-33ad-9856-9b4194e2be02},\n created = {2022-06-09T15:27:47.230Z},\n accessed = {2022-06-09},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-06-09T15:27:48.033Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {tumuklu:scitech:22},\n private_publication = {false},\n abstract = {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 bibtype = {inproceedings},\n author = {Tumuklu, Ozgur and Bellan, Josette},\n doi = {10.2514/6.2022-2017},\n booktitle = {AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2022}\n}

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\n \n\n \n \n Tumuklu, O.; Bellan, J.; and Hanquist, K.\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 In Rarefied Gas Dynamics, 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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@inproceedings{\n title = {A hybrid DSMC-continuum formulation for jet expansion into rarefied flows},\n type = {inproceedings},\n year = {2022},\n id = {6194fd39-a44b-32a0-bc31-97e66c347b02},\n created = {2022-06-09T15:27:48.830Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-06-09T15:29:44.159Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {tumuklu:rgd:2022},\n private_publication = {false},\n bibtype = {inproceedings},\n author = {Tumuklu, O and Bellan, J and Hanquist, K},\n booktitle = {Rarefied Gas Dynamics}\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 AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2022, 2022. AIAA Paper 2022-1169\n \n\n\n\n
\n\n\n\n \n \n $\"Attitude$ Paper\n \n \n \n $\"Attitude$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\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{\n title = {Attitude Reconstruction of Free-Flight CFD Generated Trajectories Using Non-Linear Pitch Damping Coefficient Curv},\n type = {inproceedings},\n year = {2022},\n websites = {https://arc.aiaa.org/doi/10.2514/6.2022-1169},\n publisher = {AIAA Paper 2022-1169},\n id = {4bff4dd8-a3d8-3628-8b5c-6198eb1b00c9},\n created = {2022-06-21T15:28:59.998Z},\n accessed = {2022-06-21},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-06-21T15:29:01.100Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {mckown:scitech:2022},\n private_publication = {false},\n abstract = {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 bibtype = {inproceedings},\n author = {McKown, Quincy E. and Kazemba, Cole D. and Stern, Eric C. and Brock, Joseph M.},\n doi = {10.2514/6.2022-1169},\n booktitle = {AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2022}\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 \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\n Journal of Fluids and Structures, 113: 103682. 8 2022.\n \n\n\n\n
\n\n\n\n \n \n $\"Study$ 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

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@article{\n title = {Study of fluid–thermal–structural interaction in high-temperature high-speed flow using multi-fidelity multi-variate surrogates},\n type = {article},\n year = {2022},\n keywords = {fsi},\n pages = {103682},\n volume = {113},\n month = {8},\n publisher = {Academic Press},\n day = {1},\n id = {f160801b-c607-36a2-953e-c99f4424094c},\n created = {2022-09-26T02:01:55.850Z},\n accessed = {2022-09-25},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-09-26T02:01:56.484Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {huang:jfs:2022},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Huang, Daning and Sadagopan, Aravinth and Düzel, Ümran and Hanquist, Kyle M.},\n doi = {10.1016/J.JFLUIDSTRUCTS.2022.103682},\n journal = {Journal of Fluids and Structures}\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 \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\n In AIAA 2022-1674, 2022. American Institute of Aeronautics and Astronautics Inc, AIAA\n \n\n\n\n
\n\n\n\n \n \n $\"Wall-Modeled$ 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

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@inproceedings{\n title = {Wall-Modeled Large-Eddy Simulations of Mach 8 Turbulent Boundary Layer and Computation of Aero-Optical Distortions},\n type = {inproceedings},\n year = {2022},\n publisher = {American Institute of Aeronautics and Astronautics Inc, AIAA},\n id = {214e259d-3df5-3e08-bcad-cd6fe1abb2b4},\n created = {2022-11-07T22:24:19.756Z},\n accessed = {2022-11-07},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-11-07T22:25:42.934Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {gomez:scitech:2022},\n private_publication = {false},\n abstract = {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 bibtype = {inproceedings},\n author = {Castillo, Pedro and Gross, Andreas and Miller, Nathan E. and Guildenbecher, Daniel R. and Lynch, Kyle P.},\n doi = {10.2514/6.2022-1674},\n booktitle = {AIAA 2022-1674}\n}

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\n \n 2021\n \n \n (23)\n \n \n

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\n \n\n \n \n Parent, B.; Hanquist, K., M.; Rajendran, P., T.; and Martin, L., E.\n\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\n In AIAA Scitech 2021 Forum, 1 2021. AIAA Paper 2021-1251\n \n\n\n\n
\n\n\n\n \n \n $\"Effect$ 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 7 downloads\n \n \n\n \n \n \n \n \n \n \n\n \n \n \n\n\n\n

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@inproceedings{\n title = {Effect of Cesium Seeding on Plasma Density in Hypersonic Boundary Layers},\n type = {inproceedings},\n year = {2021},\n month = {1},\n publisher = {AIAA Paper 2021-1251},\n id = {b6599607-7f9f-3465-ae75-c7e5f4d4e2d6},\n created = {2021-01-05T20:43:35.056Z},\n accessed = {2021-01-05},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-07-19T22:35:37.731Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {parent:scitech:2021},\n private_publication = {false},\n abstract = {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 bibtype = {inproceedings},\n author = {Parent, Bernard and Hanquist, Kyle M. and Rajendran, Prasanna T. and Martin, Liza E.},\n doi = {10.2514/6.2021-1251},\n booktitle = {AIAA Scitech 2021 Forum}\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 \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\n In AIAA Scitech 2021 Forum, 1 2021. AIAA Paper 2021-1610\n \n\n\n\n
\n\n\n\n \n \n $\"Assessment$ Paper\n \n \n \n $\"Assessment$ Website\n \n \n\n \n \n doi\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{\n title = {Assessment of High-Temperature Effects on Hypersonic Aerothermoelastic Analysis using Multi-Fidelity Multi-Variate Surrogates},\n type = {inproceedings},\n year = {2021},\n websites = {https://arc.aiaa.org/doi/10.2514/6.2021-1610},\n month = {1},\n publisher = {AIAA Paper 2021-1610},\n id = {69f83e72-ca48-36ad-9d9c-0961a4bb4ec6},\n created = {2021-01-05T20:43:35.491Z},\n accessed = {2021-01-05},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-01-06T00:27:17.172Z},\n read = {true},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {sadagopan:scitech:2021},\n private_publication = {false},\n abstract = {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 bibtype = {inproceedings},\n author = {Sadagopan, Aravinth and Huang, Daning and Martin, Liza E. and Hanquist, Kyle M.},\n doi = {10.2514/6.2021-1610},\n booktitle = {AIAA Scitech 2021 Forum}\n}

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\n \n\n \n \n Venegas, C., V.; and Huang, D.\n\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\n In AIAA SciTech Forum, 2021. AIAA Paper 2021-1707\n \n\n\n\n
\n\n\n\n \n \n $\"Expedient$ 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

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@inproceedings{\n title = {Expedient Hypersonic Aerothermal Prediction for Aerothermoelastic Analysis Via Field Inversion and Machine Learning},\n type = {inproceedings},\n year = {2021},\n publisher = {AIAA Paper 2021-1707},\n id = {0293a27c-420b-381a-9626-60c492395665},\n created = {2021-03-08T05:19:54.193Z},\n accessed = {2021-03-07},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-03-08T05:20:43.464Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {venegas:scitech:2021},\n private_publication = {false},\n abstract = {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 bibtype = {inproceedings},\n author = {Venegas, Carlos Vargas and Huang, Daning},\n doi = {10.2514/6.2021-1707},\n booktitle = {AIAA SciTech Forum}\n}

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\n \n\n \n \n Sasidharan, V.; and Duvvuri, S.\n\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\n Journal of Fluid Mechanics, 913. 2021.\n \n\n\n\n
\n\n\n\n \n \n $\"Large-$ 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

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@article{\n title = {Large- and small-amplitude shock-wave oscillations over axisymmetric bodies in high-speed flow},\n type = {article},\n year = {2021},\n keywords = {high-speed flow,shock waves},\n volume = {913},\n publisher = {Cambridge University Press},\n id = {7bce9135-4234-393a-a5ac-6dfd3937748d},\n created = {2021-07-12T05:08:41.165Z},\n accessed = {2021-07-11},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-07-12T10:41:10.827Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {sasidharan:jfm:2021},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Sasidharan, Vaisakh and Duvvuri, Subrahmanyam},\n doi = {10.1017/JFM.2021.115},\n journal = {Journal of Fluid Mechanics}\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 \n Progress Toward High Power Output in Thermionic Energy Converters.\n \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 $\"Progress$ 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

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@article{\n title = {Progress Toward High Power Output in Thermionic Energy Converters},\n type = {article},\n year = {2021},\n keywords = {efficiency,heat transfer,power density,thermionic energy conversion},\n volume = {8},\n publisher = {John Wiley & Sons, Ltd},\n id = {065ee8ac-14a5-3e50-93c4-94ee797e465c},\n created = {2021-07-22T16:01:40.986Z},\n accessed = {2021-07-22},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-07-22T16:01:51.263Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {campbell:as:2021},\n private_publication = {false},\n abstract = {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 (<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 >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 bibtype = {article},\n author = {Campbell, Matthew F. and Celenza, Thomas J. and Schmitt, Felix and Schwede, Jared W. and Bargatin, Igor},\n doi = {10.1002/ADVS.202003812},\n journal = {Advanced Science},\n number = {9}\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

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@article{\n title = {Inequitable Access to Graduate School Is Holding Back the Economy},\n type = {article},\n year = {2021},\n id = {175376cc-768d-321b-8eed-38f501d7b839},\n created = {2021-07-23T19:38:45.719Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-07-23T19:38:45.719Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {ortega:2021},\n private_publication = {false},\n bibtype = {article},\n author = {Ortega, Suzanne T},\n journal = {Barron's}\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 \n SU2-NEMO: An Open-Source Framework for Nonequilibrium Flows.\n \n \n \n \n\n\n \n\n\n\n In SU2 Conference 2021, 2021. \n \n\n\n\n
\n\n\n\n \n \n $\"SU2-NEMO:$ Website\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{\n title = {SU2-NEMO: An Open-Source Framework for Nonequilibrium Flows},\n type = {inproceedings},\n year = {2021},\n websites = {https://youtu.be/F1cua7NFId4},\n id = {1faaf3c4-90e9-3740-8696-bdb7ccc2a15d},\n created = {2021-08-16T14:41:15.206Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-12-27T18:14:30.735Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {su2:2021},\n private_publication = {false},\n bibtype = {inproceedings},\n author = {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 booktitle = {SU2 Conference 2021}\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 AIAA Scitech 2021 Forum, pages 1-16, 2021. American Institute of Aeronautics and Astronautics Inc, AIAA\n \n\n\n\n
\n\n\n\n \n \n $\"Influence$ Paper\n \n \n \n $\"Influence$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\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{\n title = {Influence of chemical kinetics models on plasma generation in hypersonic flight},\n type = {inproceedings},\n year = {2021},\n pages = {1-16},\n websites = {https://arc.aiaa.org/doi/abs/10.2514/6.2021-0057},\n publisher = {American Institute of Aeronautics and Astronautics Inc, AIAA},\n id = {d3900735-243a-3b08-bce9-db98638dc740},\n created = {2021-08-31T00:22:34.211Z},\n accessed = {2021-08-30},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-08-31T00:22:38.507Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {sawicki:scitech:2021},\n private_publication = {false},\n abstract = {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 bibtype = {inproceedings},\n author = {Sawicki, Pawel and Chaudhry, Ross S. and Boyd, Iain D.},\n doi = {10.2514/6.2021-0057},\n booktitle = {AIAA Scitech 2021 Forum}\n}

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\n \n\n \n \n Neely, A.\n\n\n \n \n \n \n \n High-Speed FSI Databaes - Unit Cases.\n \n \n \n \n\n\n \n\n\n\n 2021.\n \n\n\n\n
\n\n\n\n \n \n $\"High-Speed$ Website\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{\n title = {High-Speed FSI Databaes - Unit Cases},\n type = {misc},\n year = {2021},\n source = {UNSW Canberra},\n websites = {https://www.unsw.adfa.edu.au/high-speed-fsi-database-unit-cases},\n id = {65c1e5c3-ea24-36fa-a3c5-31cac6227616},\n created = {2021-10-26T20:59:39.749Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-10-26T21:01:19.111Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {fsi:database},\n private_publication = {false},\n bibtype = {misc},\n author = {Neely, Andrew}\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. 9 2021.\n \n\n\n\n
\n\n\n\n \n \n $\"Experimental$ Paper\n \n \n \n $\"Experimental$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\n \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{\n title = {Experimental Study of Aeroelastic Response and Performance of a Hypersonic Intake Ramp},\n type = {article},\n year = {2021},\n keywords = {Aeroelastic Response,Boundary Layer Separation,Cantilever Beam,Hysteresis,Mach Cones,Pitot Probes,Pressure Sensitive Paint,Pressure Transducers,Reynolds Averaged Navier Stokes,Structural Response},\n pages = {1-14},\n websites = {https://arc.aiaa.org/doi/abs/10.2514/1.B38348},\n month = {9},\n publisher = {American Institute of Aeronautics and Astronautics},\n day = {16},\n id = {387fcc27-d329-323e-bcd6-c7776b5f5aeb},\n created = {2021-10-26T21:58:25.000Z},\n accessed = {2021-10-26},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-10-26T21:58:25.612Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {bhattrai:jpp:2021},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Bhattrai, Sudip and McQuellin, Liam P. and Currao, Gaetano M. D. and Neely, Andrew J. and Buttsworth, David R.},\n doi = {10.2514/1.B38348},\n journal = {Journal of Propulsion and Power}\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 \n Wingtip Jets Effects on Flow Entrainment and Aerodynamic Loads.\n \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
\n\n\n\n \n \n $\"Wingtip$ Paper\n \n \n \n $\"Wingtip$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\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{\n title = {Wingtip Jets Effects on Flow Entrainment and Aerodynamic Loads},\n type = {inproceedings},\n year = {2021},\n websites = {https://arc.aiaa.org/doi/abs/10.2514/6.2021-2812},\n publisher = {AIAA Paper 2021-2812},\n id = {54ab848e-806e-3483-a380-ea3b369e5539},\n created = {2021-12-27T18:06:18.419Z},\n accessed = {2021-12-24},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-12-27T18:06:19.343Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {footohi:aviation:2021},\n private_publication = {false},\n abstract = {This work presents experimental and computational investigations of effects of wingtip jets on flow and aerodynamic loads. Wind tunnel experiments were conducted using NACA 0012 wing model with an internal flow chamber and jet slots at the tip. Tests were carried out at 5, 10, and 15 m/s and at an angle of attack of 7.5 degrees. Average aerodynamic forces and moments were recorded using six-component external balance. To complement the experimental approach, studies were performed using computational fluid dynamics (CFD) of the blowing jet near wingtips to better understand the effects on the flow field and wing performance. These simulations were performed using a compressible Reynold's Averaged Navier-Stokes (RANS) solver and investigated similar conditions used in the experimental setup. Changes in spanwise velocity show critical differences between the jet on and off cases and provide insight into the difference in lift. The jet causes a negligible change to the spanwise velocity below the airfoil, and significantly reduces and even reverses the spanwise velocity above the airfoil. This reversal of the spanwise flow is due to the air entrainment caused by the jet. Under the steady blowing, the wingtip vortex is displaced upward and outward from the wingtip. Results show that the blowing jet from the wingtip reduces the pressure on the top of the wing whereas the effect on the pressure on the bottom of the wing is minimal. Observed changes in pressure distribution explain forces and moments changes, specifically the total lift and drag increase. I. Nomenclature AR = aspect ratio í µí° ¶ í µí°¹ = aerodynamic force coefficient í µí° ¶ í µí°¹ * = aerodynamic force coefficient with jet force subtracted í µí° ¶ í µí± = aerodynamic moment coefficient í µí° ¶ í µí± * = aerodynamic moment coefficient with jet force subtracted í µí° ¶ í µí°· = coefficient of drag í µí° ¶ í µí°· *},\n bibtype = {inproceedings},\n author = {Footohi, Parisa and Mozzone, Luciano and Shkarayev, Sergey V. and Hanquist, Kyle M.},\n doi = {10.2514/6.2021-2812},\n booktitle = {AIAA AVIATION 2021 FORUM}\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.\n\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\n Journal of Thermophysics and Heat Transfer,1-20. 12 2021.\n \n\n\n\n
\n\n\n\n \n \n $\"Kinetic$ 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

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@article{\n title = {Kinetic and Continuum Modeling of High-Temperature Oxygen and Nitrogen Binary Mixtures},\n type = {article},\n year = {2021},\n pages = {1-20},\n month = {12},\n publisher = {American Institute of Aeronautics and Astronautics},\n day = {20},\n id = {2bb3526f-ea65-3278-842c-34f6107aa529},\n created = {2021-12-27T18:19:38.653Z},\n accessed = {2021-12-27},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-12-27T18:19:39.545Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {gimelshein:jtht:2021},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {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},\n doi = {10.2514/1.T6258},\n journal = {Journal of Thermophysics and Heat Transfer}\n}

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\n \n\n \n \n Parent, B.; and Hanquist, K., M.\n\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\n International Journal of Computational Fluid Dynamics, 35(5): 331-348. 2021.\n \n\n\n\n
\n\n\n\n \n \n $\"Plasma$ 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 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{\n title = {Plasma Sheath Modelling for Computational Aerothermodynamics and Magnetohydrodynamics},\n type = {article},\n year = {2021},\n keywords = {plasma},\n pages = {331-348},\n volume = {35},\n publisher = {Taylor & Francis},\n id = {932b180b-a4cb-3ecd-a8b3-9e3c0e82f11e},\n created = {2021-12-27T18:24:57.642Z},\n accessed = {2021-12-27},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-09-25T21:50:54.115Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {parent:ijcfd:2021},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Parent, Bernard and Hanquist, Kyle M.},\n doi = {10.1080/10618562.2021.1949456},\n journal = {International Journal of Computational Fluid Dynamics},\n number = {5}\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 \n Evaluation of Computational Models for Electron Transpiration Cooling.\n \n \n \n \n\n\n \n\n\n\n Aerospace, 8(9). 9 2021.\n \n\n\n\n
\n\n\n\n \n \n $\"Evaluation$ 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

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@article{\n title = {Evaluation of Computational Models for Electron Transpiration Cooling},\n type = {article},\n year = {2021},\n keywords = {etc,own},\n volume = {8},\n month = {9},\n publisher = {Multidisciplinary Digital Publishing Institute},\n day = {2},\n id = {c8c7f846-5f3c-30dc-89b9-b8cc9409aad7},\n created = {2021-12-27T18:27:29.912Z},\n accessed = {2021-12-27},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-12-28T17:00:01.065Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {campbell:aero:2021},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Campbell, Nicholas S. and Hanquist, Kyle and Morin, Andrew and Meyers, Jason and Boyd, Iain},\n doi = {10.3390/AEROSPACE8090243},\n journal = {Aerospace},\n number = {9}\n}

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\n \n\n \n \n Liza, M.; Burton, G.; and Hanquist, K.\n\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\n In Bulletin of the American Physical Society, volume Volume 66, Number 17, 2021. American Physical Society\n \n\n\n\n
\n\n\n\n \n \n $\"Examining$ Website\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

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@inproceedings{\n title = {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 type = {inproceedings},\n year = {2021},\n volume = {Volume 66, Number 17},\n websites = {https://meetings.aps.org/Meeting/DFD21/Session/H04.6},\n publisher = {American Physical Society},\n id = {20b92c05-dbfa-3a72-ae85-3930263e8c8c},\n created = {2022-01-18T03:39:50.023Z},\n accessed = {2022-01-17},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-01-18T03:39:50.023Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {liza:aps:2021},\n private_publication = {false},\n bibtype = {inproceedings},\n author = {Liza, Martin and Burton, Gregory and Hanquist, Kyle},\n booktitle = {Bulletin of the American Physical Society}\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 \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\n AIAA Journal, 59(12): 4905-4916. 12 2021.\n \n\n\n\n
\n\n\n\n \n \n $\"Parametric$ 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 \n \n \n \n \n\n\n\n

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@article{\n title = {Parametric study of nonequilibrium shock interference patterns over a fuselage-and-wing conceptual vehicle},\n type = {article},\n year = {2021},\n keywords = {Aerodynamic Coefficients,Attached Shock Wave,Boundary Layer Interaction,CFD Simulation,High Lift Device,Lift Coefficient,Mesh Generation,Nonequilibrium Flows,Temperature Effects,Vibrational Energy},\n pages = {4905-4916},\n volume = {59},\n month = {12},\n publisher = {AIAA International},\n day = {1},\n id = {658c3bcf-9429-3785-8c11-113104209321},\n created = {2022-04-13T19:37:07.878Z},\n accessed = {2022-04-13},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-04-13T19:51:45.202Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {garbacz:aj:2021},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Garbacz, Catarina and Morgado, Fábio and Fossati, Marco and Maier, Walter T. and Munguía, Brian C. and Alonso, Juan J. and Loseille, Adrien},\n doi = {10.2514/1.J060470},\n journal = {AIAA Journal},\n number = {12}\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. 7 2021.\n \n\n\n\n
\n\n\n\n \n \n $\"SU2-NEMO:$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\n \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{\n title = {SU2-NEMO: An Open-Source Framework for High-Mach Nonequilibrium Multi-Species Flows},\n type = {article},\n year = {2021},\n keywords = {aerothermodynamics,computational fluid dynamics,high,hypersonic flight,nonequilibrium flows,temperature effects},\n pages = {193},\n volume = {8},\n websites = {https://www.mdpi.com/2226-4310/8/7/193/htm,https://www.mdpi.com/2226-4310/8/7/193},\n month = {7},\n publisher = {Multidisciplinary Digital Publishing Institute},\n day = {16},\n id = {8fdb433d-8de0-361d-9ec5-f289d272dd3b},\n created = {2022-06-07T20:51:57.911Z},\n accessed = {2022-06-07},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-06-07T20:51:57.911Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {maier:a:2021},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Maier, Walter T. and Needels, Jacob T. and Garbacz, Catarina and Morgado, Fábio and Alonso, Juan J. and Fossati, Marco},\n doi = {10.3390/AEROSPACE8070193},\n journal = {Aerospace 2021, Vol. 8, Page 193},\n number = {7}\n}

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\n \n\n \n \n Parent, B.\n\n\n \n \n \n \n \n Electron heating and cooling in hypersonic flows.\n \n \n \n \n\n\n \n\n\n\n Physics of Fluids, 33(4): 046105. 4 2021.\n \n\n\n\n
\n\n\n\n \n \n $\"Electron$ 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

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@article{\n title = {Electron heating and cooling in hypersonic flows},\n type = {article},\n year = {2021},\n pages = {046105},\n volume = {33},\n month = {4},\n publisher = { AIP Publishing LLC AIP Publishing },\n day = {16},\n id = {629ed2f7-d997-3eae-b293-e0b870401b14},\n created = {2022-06-08T18:08:50.944Z},\n accessed = {2022-06-08},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-06-08T18:08:51.705Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {parent:pof:2021},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Parent, B.},\n doi = {10.1063/5.0046197},\n journal = {Physics of Fluids},\n number = {4}\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). 3 2021.\n \n\n\n\n
\n\n\n\n \n \n $\"Preventing$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\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{\n title = {Preventing a communication blackout in spacecraft during reentry},\n type = {article},\n year = {2021},\n volume = {2021},\n websites = {https://aip.scitation.org/doi/abs/10.1063/10.0003770},\n month = {3},\n publisher = { AIP Publishing LLC AIP Publishing },\n day = {2},\n id = {887e3e61-9074-3a64-9130-c4235da9965f},\n created = {2022-06-08T18:39:33.932Z},\n accessed = {2022-06-08},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-06-08T18:39:33.932Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {bandari:sl:2021},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Bandari, Anashe},\n doi = {10.1063/10.0003770},\n journal = {Scilight},\n number = {10}\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. 6 2021.\n \n\n\n\n
\n\n\n\n \n \n $\"Effect$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\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{\n title = {Effect of slip on vortex shedding from a circular cylinder in a gas flow},\n type = {article},\n year = {2021},\n pages = {063402},\n volume = {6},\n websites = {https://journals.aps.org/prfluids/abstract/10.1103/PhysRevFluids.6.063402},\n month = {6},\n publisher = {American Physical Society},\n day = {1},\n id = {af7982c4-e751-3aa1-96ff-70c89c6ccb19},\n created = {2022-06-13T17:37:50.167Z},\n accessed = {2022-06-13},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-06-13T17:37:50.167Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {gallis:prf:2021},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Gallis, M. A. and Torczynski, J. R.},\n doi = {10.1103/PHYSREVFLUIDS.6.063402},\n journal = {Physical Review Fluids},\n number = {6}\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 18th International Planetary Probe Workshop, 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

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@inproceedings{\n title = {Interpretation of Vehicle Tumbling Predictions From 6-DOF Entry and Descent Simulation},\n type = {inproceedings},\n year = {2021},\n id = {fd34cfa3-61c5-3ebb-af58-48645e569234},\n created = {2022-06-21T16:01:29.102Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-06-21T16:01:29.102Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {needels:ippw:2021},\n private_publication = {false},\n bibtype = {inproceedings},\n author = {Needels, J. and Gage, P. and Hill, J.},\n booktitle = {18th International Planetary Probe Workshop}\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 AIAA Scitech 2021 Forum, pages 1-10, 2021. AIAA Paper 2021-1876\n \n\n\n\n
\n\n\n\n \n \n $\"Performance$ Paper\n \n \n \n $\"Performance$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\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{\n title = {Performance of an sfrj with an aft-mixing section utilizing bypass air},\n type = {inproceedings},\n year = {2021},\n pages = {1-10},\n websites = {https://arc.aiaa.org/doi/10.2514/6.2021-1876},\n publisher = {AIAA Paper 2021-1876},\n id = {72e15ff3-4c7c-3717-aaa3-a099764afb03},\n created = {2022-09-14T18:36:51.752Z},\n accessed = {2022-09-14},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-09-14T18:36:52.335Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {evans:scitech:2021},\n private_publication = {false},\n abstract = {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 bibtype = {inproceedings},\n author = {Evans, Jay V. and Senior, William C.B. and Gejji, Rohan M. and Strahan, Nicholas L. and Slabaugh, Carson D.},\n doi = {10.2514/6.2021-1876},\n booktitle = {AIAA Scitech 2021 Forum}\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 \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\n Physics of Fluids, 33(3). 3 2021.\n \n\n\n\n
\n\n\n\n \n \n $\"How$ 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

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@article{\n title = {How to build coarse-grain transport models consistent from the kinetic to fluid regimes},\n type = {article},\n year = {2021},\n volume = {33},\n month = {3},\n publisher = { AIP Publishing LLC AIP Publishing },\n day = {11},\n id = {9b4751bc-e036-3ad9-b6be-e9de187c6127},\n created = {2022-11-09T19:34:13.607Z},\n accessed = {2022-11-04},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-11-09T19:34:14.116Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {torres:pof:2021},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Torres, Erik and Bellas-Chatzigeorgis, Georgios and Magin, Thierry E.},\n doi = {10.1063/5.0037133},\n journal = {Physics of Fluids},\n number = {3}\n}

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\n \n 2020\n \n \n (21)\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. \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{\n title = {Modeling High-Temperature Flow Field Effects Relevant to Fluid-Thermal-Structural Interactions},\n type = {inproceedings},\n year = {2020},\n id = {735955e5-7ed0-3c09-8b63-9194075c2bb1},\n created = {2021-01-05T20:43:34.857Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-01-05T20:43:34.857Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {hanquist:jannaf:2020},\n source_type = {inproceedings},\n private_publication = {false},\n bibtype = {inproceedings},\n author = {Hanquist, Kyle M and Düzel, Ümran and Liza, Martin E and Sadagopan, Aravinth and Huang, Daning},\n booktitle = {Joint Meeting of the Combustion, Airbreathing Propulsion, Exhaust Plume and Signatures, and Energetic Systems Hazards subcommittees, and Programmatic and Industrial Base meeting}\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 \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\n Physics of Fluids, 32(7): 1-21. 2020.\n \n\n\n\n
\n\n\n\n \n \n $\"Shock-tube$ 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 1 download\n \n \n\n \n \n \n \n \n \n \n\n \n \n \n\n\n\n

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@article{\n title = {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 type = {article},\n year = {2020},\n pages = {1-21},\n volume = {32},\n publisher = {American Institute of Physics Inc.},\n id = {a9087f22-52cc-3755-a1fa-fbf0f70e6e47},\n created = {2021-01-05T20:43:34.966Z},\n accessed = {2021-01-04},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-09-26T19:12:30.202Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {streicher:pof:2020},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Streicher, Jesse W. and Krish, Ajay and Hanson, Ronald K. and Hanquist, Kyle M. and Chaudhry, Ross S. and Boyd, Iain D.},\n doi = {10.1063/5.0012426},\n journal = {Physics of Fluids},\n number = {7}\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 \n Fully-Coupled Simulation of Plasma Discharges, Turbulence, and Combustion in a Scramjet Combustor.\n \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 $\"Fully-Coupled$ 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 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{\n title = {Fully-Coupled Simulation of Plasma Discharges, Turbulence, and Combustion in a Scramjet Combustor},\n type = {inproceedings},\n year = {2020},\n publisher = {AIAA Paper 2020-3230},\n id = {47283358-2860-34a5-a011-4186488e7868},\n created = {2021-01-05T20:43:35.171Z},\n accessed = {2021-01-04},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-09-25T21:51:02.917Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {parent:avi:2020},\n private_publication = {false},\n abstract = {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 bibtype = {inproceedings},\n author = {Parent, Bernard and Omprakas, Ajjay and Hanquist, Kyle M.},\n doi = {10.2514/6.2020-3230},\n booktitle = {AIAA Aviation and Aeronautics Forum and Exposition},\n keywords = {plasma}\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 \n Detailed Thermochemical Modeling of O2-Ar in Reflected Shock Tube Flows.\n \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 $\"Detailed$ 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

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@inproceedings{\n title = {Detailed Thermochemical Modeling of O2-Ar in Reflected Shock Tube Flows},\n type = {inproceedings},\n year = {2020},\n publisher = {AIAA Paper 2020-3275},\n id = {1957fbf9-e321-39a0-beaf-12034f182566},\n created = {2021-01-05T20:43:35.492Z},\n accessed = {2021-01-04},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-08-16T14:43:43.879Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {hanquist:aviation:2020},\n source_type = {inproceedings},\n private_publication = {false},\n abstract = {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 bibtype = {inproceedings},\n author = {Hanquist, Kyle M. and Chaudhry, Ross S. and Boyd, Iain D. and Streicher, Jesse W. and Krish, Ajay and Hanson, Ronald K.},\n doi = {10.2514/6.2020-3275},\n booktitle = {AIAA Aviation and Aeronautics Forum and Exposition}\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 \n Assessment of Thermochemistry Modeling for Hypersonic Flow over a Double Cone.\n \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 $\"Assessment$ Paper\n \n \n \n $\"Assessment$ Website\n \n \n\n \n \n doi\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

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@article{\n title = {Assessment of Thermochemistry Modeling for Hypersonic Flow over a Double Cone},\n type = {article},\n year = {2020},\n pages = {538-547},\n volume = {34},\n websites = {https://arc.aiaa.org/doi/10.2514/1.T5792},\n publisher = {American Institute of Aeronautics and Astronautics Inc.},\n id = {800cc515-9986-349f-9630-b7f95079f019},\n created = {2021-01-05T20:43:35.702Z},\n accessed = {2021-01-04},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-01-05T20:43:53.561Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {holloway:jtht:2020},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Holloway, Michael E. and Hanquist, Kyle M. and Boyd, Iain D.},\n doi = {10.2514/1.T5792},\n journal = {Journal of Thermophysics and Heat Transfer},\n number = {3}\n}

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\n \n\n \n \n Sadagopan, A.; Huang, D.; and Hanquist, K.\n\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\n In AIAA Science and Technology Forum and Exposition, 2020. AIAA Paper 2020-0937\n \n\n\n\n
\n\n\n\n \n \n $\"Impact$ 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

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@inproceedings{\n title = {Impact of High-Temperature Effects on the Aerothermoelastic Behavior of Composite Skin Panels in Hypersonic Flow},\n type = {inproceedings},\n year = {2020},\n publisher = {AIAA Paper 2020-0937},\n city = {Orlando, FL},\n id = {8b04fa5f-6888-3cc5-abca-2a007da93fa1},\n created = {2021-01-05T20:43:35.703Z},\n accessed = {2021-01-04},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-01-05T20:43:52.536Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {sadagopan:scitech:2020},\n source_type = {inproceedings},\n private_publication = {false},\n abstract = {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 bibtype = {inproceedings},\n author = {Sadagopan, Aravinth and Huang, Daning and Hanquist, Kyle},\n doi = {10.2514/6.2020-0937},\n booktitle = {AIAA Science and Technology Forum and Exposition}\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 \n Mutation++: MUlticomponent Thermodynamic And Transport properties for IONized gases in C++.\n \n \n \n \n\n\n \n\n\n\n SoftwareX, 12: 100575. 7 2020.\n \n\n\n\n
\n\n\n\n \n \n $\"Mutation++:$ 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

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@article{\n title = {Mutation++: MUlticomponent Thermodynamic And Transport properties for IONized gases in C++},\n type = {article},\n year = {2020},\n keywords = {Gas-surface interaction,Multiphase equilibrium,Partially ionized gases,Thermochemical nonequilibrium},\n pages = {100575},\n volume = {12},\n month = {7},\n publisher = {Elsevier B.V.},\n day = {1},\n id = {a6f7be08-e8a9-3816-a3d9-f572ea412e05},\n created = {2021-02-23T23:57:03.888Z},\n accessed = {2021-02-23},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-02-23T23:57:06.021Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {scoggins:sx:2021},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Scoggins, James B. and Leroy, Vincent and Bellas-Chatzigeorgis, Georgios and Dias, Bruno and Magin, Thierry E.},\n doi = {10.1016/j.softx.2020.100575},\n journal = {SoftwareX}\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{\n title = {Numerical Study of Shock Interference Patterns for Gas Flows with Thermal Nonequilibrium and Finite-Rate Chemistry},\n type = {inproceedings},\n year = {2020},\n publisher = {AIAA Paper 2020-1805},\n id = {3cdedb58-79db-3a9b-b83c-7d86b377bb77},\n created = {2021-05-29T00:13:18.916Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-07-23T21:07:16.854Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {garbacz:scitech:2020},\n source_type = {inproceedings},\n private_publication = {false},\n bibtype = {inproceedings},\n author = {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 doi = {10.2514/6.2020-1805}\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 AIAA Scitech 2020 Forum, 1 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{\n title = {Analytical Approach for Aero-Optical and Atmospheric Effects in Supersonic Flow Fields},\n type = {inproceedings},\n year = {2020},\n month = {1},\n publisher = {AIAA 2020-0684},\n city = {Orlando, FL},\n id = {79892581-f449-3180-ac77-fa2922022e28},\n created = {2021-05-31T19:19:31.341Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-05-31T19:19:31.341Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {gupta:scitech:2020},\n source_type = {inproceedings},\n private_publication = {false},\n bibtype = {inproceedings},\n author = {Gupta, Anubhav and Argrow, Brian},\n booktitle = {AIAA Scitech 2020 Forum}\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 Gallery of Fluid Motion - APS Division of Fluid Dynamics, 11 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{\n title = {Video: Pulsating shock waves at Mach 6},\n type = {inproceedings},\n year = {2020},\n month = {11},\n publisher = {American Physical Society (APS)},\n day = {19},\n id = {1ef3debb-96e9-3dee-b085-7bb1d34ceb0f},\n created = {2021-05-31T20:49:11.751Z},\n accessed = {2021-05-31},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-05-31T20:49:11.751Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {sasidharan:aps:2020},\n private_publication = {false},\n bibtype = {inproceedings},\n author = {Sasidharan, Vaisakh and Duvvuri, Subrahmanyam},\n doi = {10.1103/aps.dfd.2020.gfm.v0015},\n booktitle = {Gallery of Fluid Motion - APS Division of Fluid Dynamics}\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 $\"Detailed$ Website\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{\n title = {Detailed Investigation of Nonequilibrium Effects on Aero-Optics in Hypersonic Flows},\n type = {techreport},\n year = {2020},\n websites = {https://chanl.arizona.edu/afrl-final-report-2020},\n institution = {University of Arizona - Air Force Research Laboratory},\n id = {d962624c-1be4-3976-b702-3be7bb9dd113},\n created = {2021-07-11T17:44:32.894Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-07-11T17:44:32.894Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {hanquist:afrl:2020},\n private_publication = {false},\n bibtype = {techreport},\n author = {Hanquist, Kyle M.}\n}

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\n \n\n \n \n Blanco, A.; and Josyula, E.\n\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\n https://doi.org/10.2514/1.J059307, 58(8): 3464-3475. 5 2020.\n \n\n\n\n
\n\n\n\n \n \n $\"Numerical$ 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 \n \n \n \n \n\n\n\n

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@article{\n title = {Numerical Modeling of Hypersonic Weakly Ionized External Flowfields with Poisson’s Equation},\n type = {article},\n year = {2020},\n keywords = {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 pages = {3464-3475},\n volume = {58},\n month = {5},\n publisher = {American Institute of Aeronautics and Astronautics},\n day = {22},\n id = {5ac7c287-e0aa-3999-ab4c-c73f4e05130d},\n created = {2021-07-19T21:38:34.630Z},\n accessed = {2021-07-19},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-07-19T21:38:43.837Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {blanco:aj:2020},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Blanco, Ariel and Josyula, Eswar},\n doi = {10.2514/1.J059307},\n journal = {https://doi.org/10.2514/1.J059307},\n number = {8}\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 AIAA Scitech 2020 Forum, 1 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{\n title = {Inductively Coupled Facility Qualification for Electron Transpiration Cooling Investigations},\n type = {inproceedings},\n year = {2020},\n keywords = {etc},\n month = {1},\n publisher = {AIAA Paper 2020-0921},\n city = {Orlando, FL},\n id = {6c102866-958e-34a4-9d61-d3e4dc956e2f},\n created = {2021-07-22T16:20:19.433Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-07-23T21:07:17.098Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {morin:scitech:2020},\n source_type = {inproceedings},\n private_publication = {false},\n bibtype = {inproceedings},\n author = {Morin, Andrew J and Osborn, Rebecca and Schindler, Jeff C and Jagun, Precious and Fletcher, Douglas G and Meyers, Jason M},\n booktitle = {AIAA Scitech 2020 Forum}\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 \n Aerodynamic Dataset Generation of a Long-Range Projectile.\n \n \n \n \n\n\n \n\n\n\n Technical Report CCDC Army Research Laboratory, 2020.\n \n\n\n\n
\n\n\n\n \n \n $\"Aerodynamic$ 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 \n \n \n \n \n \n \n \n \n \n\n\n\n

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@techreport{\n title = {Aerodynamic Dataset Generation of a Long-Range Projectile},\n type = {techreport},\n year = {2020},\n keywords = {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 city = {ARL-TR-9019},\n institution = {CCDC Army Research Laboratory},\n id = {109556ad-e1fa-3a1c-ab77-6fd05f8931a3},\n created = {2021-10-18T18:00:47.255Z},\n accessed = {2021-10-18},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-10-18T18:00:47.770Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {vasile:2020},\n private_publication = {false},\n bibtype = {techreport},\n author = {Vasile, Joseph D and Bryson, Joshua T and Sahu, Jubaraj and Paul, Justin L and Gruenwald, Benjamin C}\n}

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\n \n\n \n \n Manuel Núñez, J.; Tutora, P.; Ángeles, M.; and Prats, M.\n\n\n \n \n \n \n \n Analysis and Simulation of a Practical Quantum Key Distribution in Python for Aerospace applications.\n \n \n \n \n\n\n \n\n\n\n Ph.D. Thesis, 2020.\n \n\n\n\n
\n\n\n\n \n \n $\"Analysis$ Website\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

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@phdthesis{\n title = {Analysis and Simulation of a Practical Quantum Key Distribution in Python for Aerospace applications},\n type = {phdthesis},\n year = {2020},\n keywords = {info:eu,repo/semantics/masterThesis},\n websites = {https://idus.us.es/handle/11441/107998},\n institution = {Universidad de Sevilla},\n department = {Departamento de Ingeniería Electrónica},\n id = {f3c3376e-d05c-3c12-93d6-dfe0c63530f7},\n created = {2021-11-12T22:55:25.119Z},\n accessed = {2021-11-12},\n file_attached = {false},\n profile_id = {54dbf64e-95b3-3e31-962f-73840c02c7c3},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-11-12T23:03:50.358Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {Núñez:DIUS:2020},\n user_context = {Master's Final Project},\n private_publication = {false},\n abstract = {Universidad de Sevilla. Máster en Ingeniería Aeronáutica},\n bibtype = {phdthesis},\n author = {Manuel Núñez, Juan and Tutora, Portillo and Ángeles, María and Prats, Martín}\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 \n Calibration probe uncertainty and validation for the hypersonic material environmental test system.\n \n \n \n \n\n\n \n\n\n\n Journal of Thermophysics and Heat Transfer, 34(2): 404-420. 1 2020.\n \n\n\n\n
\n\n\n\n \n \n $\"Calibration$ 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 \n \n \n \n \n\n\n\n

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@article{\n title = {Calibration probe uncertainty and validation for the hypersonic material environmental test system},\n type = {article},\n year = {2020},\n keywords = {CFD Simulation,Collocation Method,Cumulative Distribution Function,Enthalpy,Heat Flux,NASA Langley Research Center,Sensitivity Analysis,Slug Calorimeters,Stagnation Pressure,Thermal Protection System},\n pages = {404-420},\n volume = {34},\n month = {1},\n publisher = {American Institute of Aeronautics and Astronautics Inc.},\n day = {21},\n id = {8fe9e6a0-b5e0-38bf-82cf-fb519796ddad},\n created = {2022-04-18T17:08:44.887Z},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-04-18T17:08:45.490Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {brune:jtht:2020},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Brune, Andrew J. and West, Thomas K. and Whit, Laura M.},\n doi = {10.2514/1.T5839},\n journal = {Journal of Thermophysics and Heat Transfer},\n number = {2}\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 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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@misc{\n title = {Covid-19 has Forced Higher Ed to Pivot to Online Learning. Here are 7 Takeaways so Far.},\n type = {misc},\n year = {2020},\n source = {The Chronicle of Higher Education},\n id = {69f4f1b8-fb12-312e-88c5-c1765837a0ad},\n created = {2022-07-26T02:24:22.903Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-07-26T02:24:22.903Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {gardner:2020},\n private_publication = {false},\n bibtype = {misc},\n author = {Gardner, L.}\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. 6 2020.\n \n\n\n\n
\n\n\n\n \n \n $\"Bayesian$ 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

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@article{\n title = {Bayesian Machine Learning Approach to the Quantification of Uncertainties on Ab Initio Potential Energy Surfaces},\n type = {article},\n year = {2020},\n pages = {5129-5146},\n volume = {124},\n month = {6},\n publisher = {American Chemical Society},\n day = {25},\n id = {fb67a90c-5a16-3e2a-9da9-ecc09cf57774},\n created = {2022-09-16T19:43:01.603Z},\n accessed = {2022-09-16},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-09-26T19:14:11.438Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {venturi:jpc:2020},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Venturi, S. and Jaffe, R. L. and Panesi, M.},\n doi = {10.1021/ACS.JPCA.0C02395},\n journal = {Journal of Physical Chemistry A},\n number = {25}\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 O2+ O System.\n \n \n \n \n\n\n \n\n\n\n Journal of Physical Chemistry A, 124(41): 8359-8372. 10 2020.\n \n\n\n\n
\n\n\n\n \n \n $\"Data-Inspired$ 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

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@article{\n title = {Data-Inspired and Physics-Driven Model Reduction for Dissociation: Application to the O2+ O System},\n type = {article},\n year = {2020},\n pages = {8359-8372},\n volume = {124},\n month = {10},\n publisher = {American Chemical Society},\n day = {15},\n id = {370fa6fc-f700-32b6-8df5-6e67c7d2a77a},\n created = {2022-09-16T19:43:26.776Z},\n accessed = {2022-09-16},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-09-26T19:14:41.443Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {venturi:jpc:2020a},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Venturi, S. and Sharma, M. P. and Lopez, B. and Panesi, M.},\n doi = {10.1021/ACS.JPCA.0C04516},\n journal = {Journal of Physical Chemistry A},\n number = {41}\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 \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\n Journal of Physical Chemistry A, 124(35): 6986-7000. 9 2020.\n \n\n\n\n
\n\n\n\n \n \n $\"State-to-State$ 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

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@article{\n title = {State-to-State Master Equation and Direct Molecular Simulation Study of Energy Transfer and Dissociation for the N2-N System},\n type = {article},\n year = {2020},\n pages = {6986-7000},\n volume = {124},\n month = {9},\n publisher = {American Chemical Society},\n day = {3},\n id = {18445ffd-2770-32a8-8025-95bec13bd79a},\n created = {2022-09-26T18:42:15.531Z},\n accessed = {2022-09-26},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-09-26T19:18:33.114Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {macdonald:jpca:2020},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {MacDonald, Robyn L. and Torres, Erik and Schwartzentruber, Thomas E. and Panesi, Marco},\n doi = {10.1021/ACS.JPCA.0C04029},\n journal = {Journal of Physical Chemistry A},\n number = {35}\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 \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\n AIAA Journal, 58(1): 278-290. 11 2020.\n \n\n\n\n
\n\n\n\n \n \n $\"Energy$ 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 \n \n \n \n \n\n\n\n

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@article{\n title = {Energy accommodation coefficient calculation methodology using state-to-state catalysis applied to hypersonic flows},\n type = {article},\n year = {2020},\n keywords = {Aerothermodynamics,Chemical Equilibrium,Computational Fluid Dynamics,Freestream Conditions,Heterogeneous Catalysis,Hypersonic Flows,Quenching,Thermal Nonequilibrium,Thermal Protection System,Vibrational Energy},\n pages = {278-290},\n volume = {58},\n month = {11},\n publisher = {AIAA International},\n day = {14},\n id = {573d6c78-1d8e-323b-ac9e-aef8b57e81a3},\n created = {2022-11-09T19:35:18.258Z},\n accessed = {2022-11-04},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-11-09T19:35:18.810Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {bellas:aj:2020},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Bellas-Chatzigeorgis, Georgios and Magin, Thierry E. and Barbante, Paolo F.},\n doi = {10.2514/1.J058543},\n journal = {AIAA Journal},\n number = {1}\n}

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\n \n 2019\n \n \n (27)\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 \n Shape Optimization of Reentry Vehicles to Minimize Heat Loading.\n \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 $\"Shape$ 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 5 downloads\n \n \n\n \n \n \n \n \n \n \n\n \n \n \n\n\n\n

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@article{\n title = {Shape Optimization of Reentry Vehicles to Minimize Heat Loading},\n type = {article},\n year = {2019},\n pages = {785-796},\n volume = {33},\n publisher = {American Institute of Aeronautics and Astronautics Inc.},\n id = {1dd0a9e4-b76b-338e-b2f4-893179440799},\n created = {2021-01-05T20:43:34.503Z},\n accessed = {2021-01-04},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-07-23T21:07:17.364Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {eyi:jtht:2019a},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Eyi, Sinan and Hanquist, Kyle M. and Boyd, Iain D.},\n doi = {10.2514/1.T5705},\n journal = {Journal of Thermophysics and Heat Transfer},\n number = {3}\n}

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\n \n\n \n \n Hanquist, K., M.; and Boyd, I., D.\n\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\n Frontiers in Physics: Plasma for Aerospace, 7(9): 1-13. 2019.\n \n\n\n\n
\n\n\n\n \n \n $\"Plasma$ 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 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{\n title = {Plasma Assisted Cooling of Hot Surfaces on Hypersonic Vehicles},\n type = {article},\n year = {2019},\n keywords = {etc},\n pages = {1-13},\n volume = {7},\n publisher = {Frontiers},\n id = {f965f79e-6b3d-3946-a303-3fda8896bfcb},\n created = {2021-01-05T20:43:34.507Z},\n accessed = {2021-01-04},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-07-23T20:58:40.856Z},\n read = {true},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {hanquist:fip:2019},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Hanquist, Kyle M. and Boyd, Iain D.},\n doi = {10.3389/fphy.2019.00009},\n journal = {Frontiers in Physics: Plasma for Aerospace},\n number = {9}\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 \n Aerothermodynamic Design Optimization of Hypersonic Vehicles.\n \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 $\"Aerothermodynamic$ 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 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{\n title = {Aerothermodynamic Design Optimization of Hypersonic Vehicles},\n type = {article},\n year = {2019},\n pages = {392-406},\n volume = {33},\n publisher = {American Institute of Aeronautics and Astronautics Inc.},\n id = {df3f453e-5e08-3ceb-836d-cc3ff86ad81d},\n created = {2021-01-05T20:43:34.711Z},\n accessed = {2021-01-04},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-09-25T21:44:31.702Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {eyi:jtht:2019},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Eyi, Sinan and Hanquist, Kyle M. and Boyd, Iain D.},\n doi = {10.2514/1.T5523},\n journal = {Journal of Thermophysics and Heat Transfer},\n number = {2},\n keywords = {thermal}\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 \n Shape Optimization of Reentry Vehicles to Minimize Heat Loading.\n \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 $\"Shape$ 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 5 downloads\n \n \n\n \n \n \n \n \n \n \n\n \n \n \n\n\n\n

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@inproceedings{\n title = {Shape Optimization of Reentry Vehicles to Minimize Heat Loading},\n type = {inproceedings},\n year = {2019},\n publisher = {AIAA Paper 2019-0973},\n city = {San Diego, CA},\n id = {e14d71ce-12c1-3d50-a6ba-1bd1d0f16b4b},\n created = {2021-01-05T20:43:35.107Z},\n accessed = {2021-01-04},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-01-05T20:43:43.489Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {eyi:scitech:2019},\n source_type = {inproceedings},\n private_publication = {false},\n abstract = {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 bibtype = {inproceedings},\n author = {Eyi, Sinan and Hanquist, Kyle M. and Boyd, Iain D.},\n doi = {10.2514/6.2019-0973},\n booktitle = {AIAA Science and Technology Forum and Exposition}\n}

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\n \n\n \n \n Hanquist, K., M.; and Boyd, I., D.\n\n\n \n \n \n \n \n Modeling of Electronically Excited Oxygen in $O_2-Ar$ Shock Tube Studies.\n \n \n \n \n\n\n \n\n\n\n In AIAA Aviation and Aeronautics Forum and Exposition, 6 2019. AIAA Paper 2019-3567\n \n\n\n\n
\n\n\n\n \n \n $\"Modeling$ 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

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@inproceedings{\n title = {Modeling of Electronically Excited Oxygen in $O_2-Ar$ Shock Tube Studies},\n type = {inproceedings},\n year = {2019},\n month = {6},\n publisher = {AIAA Paper 2019-3567},\n day = {17},\n city = {Atlanta, GA},\n id = {d6feb856-1a6c-38fe-95c8-909bc6304524},\n created = {2021-01-05T20:43:35.461Z},\n accessed = {2021-01-04},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-05-31T20:07:05.835Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {hanquist:aviation:2019},\n source_type = {inproceedings},\n private_publication = {false},\n abstract = {The successful development of hypersonic vehicles requires detailed knowledge of the flow physics around the vehicle. Specifically, an understanding of the thermochemical nonequi-librium behavior is crucial for this flight regime. Additionally, 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. However, there is limited experimental data to assess the current nonequilibrium modeling approaches. Recently, the Hanson Group at Stanford University measured the formation of electronically excited atomic oxygen behind reflected shock waves using cavity-enhanced absorption spectroscopy. The motivation of this work is to develop a modeling approach that can be assessed using these experiments. In the present work, 1D post normal shock flow calculations of both pure and diluted molecular oxygen in argon are carried out and used to analyze existing shock tube experiments. State-of-the-art thermochemical nonequi-librium models, including two-temperature (2T) and multitemperature-collisional-radiative (MTCR) models are adopted in these post normal shock flow analyses. The 2T approach models the excited states using Boltzmann statistics at the vibrational temperature. The MTCR uses a four temperature approach (translational, rotational, vibrational, and electronic). The non-Boltzmann behavior of the excited states is modeled by including the relevant collisional and radiative mechanisms and then solving for the excited state concentrations using an electronic master equation coupling model. I. Nomenclature c = Thermal velocity D = Dissociation energy e = Specific energy E = Energy g = Degeneracy h = Enthalpy I = Ionization energy k = Boltzmann's constant K = Excitation rate m = Mass N a = Avogadro's number n = Number density p = Pressure Q = Partition function Q r ad = Radiative energy loss q = Franck-Condon factor t = Time T = Temperature u = Velocity v = Collision frequency x = Distance from shock * Research Fellow and Lecturer, Member AIAA.},\n bibtype = {inproceedings},\n author = {Hanquist, Kyle M. and Boyd, Iain D.},\n doi = {10.2514/6.2019-3567},\n booktitle = {AIAA Aviation and Aeronautics Forum and Exposition}\n}

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\n The successful development of hypersonic vehicles requires detailed knowledge of the flow physics around the vehicle. Specifically, an understanding of the thermochemical nonequi-librium behavior is crucial for this flight regime. Additionally, 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. However, there is limited experimental data to assess the current nonequilibrium modeling approaches. Recently, the Hanson Group at Stanford University measured the formation of electronically excited atomic oxygen behind reflected shock waves using cavity-enhanced absorption spectroscopy. The motivation of this work is to develop a modeling approach that can be assessed using these experiments. In the present work, 1D post normal shock flow calculations of both pure and diluted molecular oxygen in argon are carried out and used to analyze existing shock tube experiments. State-of-the-art thermochemical nonequi-librium models, including two-temperature (2T) and multitemperature-collisional-radiative (MTCR) models are adopted in these post normal shock flow analyses. The 2T approach models the excited states using Boltzmann statistics at the vibrational temperature. The MTCR uses a four temperature approach (translational, rotational, vibrational, and electronic). The non-Boltzmann behavior of the excited states is modeled by including the relevant collisional and radiative mechanisms and then solving for the excited state concentrations using an electronic master equation coupling model. I. Nomenclature c = Thermal velocity D = Dissociation energy e = Specific energy E = Energy g = Degeneracy h = Enthalpy I = Ionization energy k = Boltzmann's constant K = Excitation rate m = Mass N a = Avogadro's number n = Number density p = Pressure Q = Partition function Q r ad = Radiative energy loss q = Franck-Condon factor t = Time T = Temperature u = Velocity v = Collision frequency x = Distance from shock * Research Fellow and Lecturer, Member AIAA.\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 \n Effect of Thermochemistry Modeling on Hypersonic Flow Over a Double Cone.\n \n \n \n \n\n\n \n\n\n\n In AIAA Science and Technology Forum and Exposition, 2019. AIAA Paper 2019-2281\n \n\n\n\n
\n\n\n\n \n \n $\"Effect$ 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

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@inproceedings{\n title = {Effect of Thermochemistry Modeling on Hypersonic Flow Over a Double Cone},\n type = {inproceedings},\n year = {2019},\n publisher = {AIAA Paper 2019-2281},\n city = {San Diego, CA},\n id = {17b6b0f3-8dbf-3584-9fa4-53d904b64062},\n created = {2021-01-05T20:43:35.659Z},\n accessed = {2021-01-04},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-01-05T20:43:51.706Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {holloway:scitech:2019},\n source_type = {inproceedings},\n private_publication = {false},\n abstract = {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 bibtype = {inproceedings},\n author = {Holloway, Michael E. and Hanquist, Kyle M. and Boyd, Iain D.},\n doi = {10.2514/6.2019-2281},\n booktitle = {AIAA Science and Technology Forum and Exposition}\n}

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\n \n\n \n \n Candler, G., V.\n\n\n \n \n \n \n \n Rate Effects in Hypersonic Flows.\n \n \n \n \n\n\n \n\n\n\n Annual Review of Fluid Mechanics, 51(1): 379-402. 2019.\n \n\n\n\n
\n\n\n\n \n \n $\"Rate$ Paper\n \n \n \n $\"Rate$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\n \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{\n title = {Rate Effects in Hypersonic Flows},\n type = {article},\n year = {2019},\n keywords = {aerothermodynamics,finite-rate processes,high-temperature gas dynamics,hypersonic aerodynamics,nonequilibrium flows},\n pages = {379-402},\n volume = {51},\n websites = {https://www.annualreviews.org/doi/10.1146/annurev-fluid-010518-040258},\n publisher = {Annual Reviews Inc.},\n id = {36b76cb1-89ff-3256-a408-547890c82fbe},\n created = {2021-02-15T18:10:50.572Z},\n accessed = {2021-02-15},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-02-15T18:10:52.595Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {candler:arfm:2019},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Candler, Graham V.},\n doi = {10.1146/annurev-fluid-010518-040258},\n journal = {Annual Review of Fluid Mechanics},\n number = {1}\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 AIAA Scitech 2019 Forum, 1 2019. AIAA Paper 2019-0789\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{\n title = {Statistical Analyses of Quasiclassical Trajectory Data for Air Dissociation},\n type = {inproceedings},\n year = {2019},\n month = {1},\n publisher = {AIAA Paper 2019-0789},\n city = {San Diego, CA},\n id = {d68dd2a2-b32d-3b7d-9485-024a3b0dbcf0},\n created = {2021-02-17T23:21:54.525Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-02-17T23:25:29.117Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {chaudhry:scitech:2019},\n source_type = {inproceedings},\n private_publication = {false},\n bibtype = {inproceedings},\n author = {Chaudhry, Ross S and Candler, Graham V},\n booktitle = {AIAA Scitech 2019 Forum}\n}

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\n \n\n \n \n Rafano Carná, S., F.; and Bevilacqua, R.\n\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\n Acta Astronautica, 156: 134-156. 3 2019.\n \n\n\n\n
\n\n\n\n \n \n $\"High$ 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

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@article{\n title = {High fidelity model for the atmospheric re-entry of CubeSats equipped with the Drag De-Orbit Device},\n type = {article},\n year = {2019},\n keywords = {Aerodynamic model,Aerothermodynamic model,Atmospheric re-entry modeling,CubeSats,Drag De-Orbit Device},\n pages = {134-156},\n volume = {156},\n month = {3},\n publisher = {Elsevier Ltd},\n day = {1},\n id = {71c35507-4705-3d77-aaac-e23c3b5ff788},\n created = {2021-03-08T00:45:55.918Z},\n accessed = {2021-03-07},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-03-08T00:46:47.932Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {rafano:aa:2019},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Rafano Carná, S. F. and Bevilacqua, R.},\n doi = {10.1016/j.actaastro.2018.05.049},\n journal = {Acta Astronautica}\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 \n An aerothermodynamic design optimization framework for hypersonic vehicles.\n \n \n \n \n\n\n \n\n\n\n Aerospace Science and Technology, 84: 339-347. 1 2019.\n \n\n\n\n
\n\n\n\n \n \n $\"An$ 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

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@article{\n title = {An aerothermodynamic design optimization framework for hypersonic vehicles},\n type = {article},\n year = {2019},\n keywords = {CST,Design optimization,Evolutionary strategies,Hypersonics},\n pages = {339-347},\n volume = {84},\n month = {1},\n publisher = {Elsevier Masson SAS},\n day = {1},\n id = {412f64f0-ccfe-3f1d-be6a-0f2122d7e8a7},\n created = {2021-05-29T00:09:06.105Z},\n accessed = {2021-05-28},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-05-29T00:09:28.945Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {giorgio:ast:2019},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Di Giorgio, Simone and Quagliarella, Domenico and Pezzella, Giuseppe and Pirozzoli, Sergio},\n doi = {10.1016/j.ast.2018.09.042},\n journal = {Aerospace Science and Technology}\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. 12 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{\n title = {Influence of vibrational non-equilibrium on the polarizability and refraction index in air: computational study},\n type = {article},\n year = {2019},\n pages = {105201},\n volume = {53},\n month = {12},\n id = {8562828d-3870-3855-acee-8b15f8e68f90},\n created = {2021-05-31T19:42:51.819Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-05-31T19:42:51.819Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {tropina:jop:2019},\n source_type = {article},\n private_publication = {false},\n bibtype = {article},\n author = {Tropina, Albina A and Wu, Yue and Limbach, Christopher M and Miles, Richard B},\n journal = {Journal of Physics D: Applied Physics},\n number = {10}\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. 7 2019.\n \n\n\n\n
\n\n\n\n \n \n $\"Assessment$ 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 \n \n \n \n \n\n\n\n

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@article{\n title = {Assessment of hypersonic flow physics on aero-optics},\n type = {article},\n year = {2019},\n keywords = {Chemical Energy,Computational Fluid Dynamics Simulation,Energy Distribution,Freestream Mach Number,Gas Constant,Nonequilibrium Flows,Optical Properties,Optical Sensor,Stagnation Region,Stagnation Streamlines},\n pages = {3885-3897},\n volume = {57},\n month = {7},\n publisher = {American Institute of Aeronautics and Astronautics Inc.},\n day = {14},\n id = {47daec9e-07e9-3cb5-982f-ec70223d5b18},\n created = {2021-05-31T22:40:22.447Z},\n accessed = {2021-05-31},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-07-12T10:41:10.513Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {mackey:aj:2019},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Mackey, Lauren E. and Boyd, Iain D.},\n doi = {10.2514/1.J057869},\n journal = {AIAA Journal},\n number = {9}\n}

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\n \n\n \n \n Burton, G., C.; Campos, A.; Jang, I.; Kavouklis, C.; and Stein, E.\n\n\n \n \n \n \n MARGOT: Large-Eddy Simulation / Direct-Numerical Simulation for Unsteady Hypersonic Aerothermodynamic Flow: A Unique CFD Tool for Local-Scale Damage Assessment.\n \n \n \n\n\n \n\n\n\n Technical Report Lawrence Livermore National Laboratory, 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

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@techreport{\n title = {MARGOT: Large-Eddy Simulation / Direct-Numerical Simulation for Unsteady Hypersonic Aerothermodynamic Flow: A Unique CFD Tool for Local-Scale Damage Assessment},\n type = {techreport},\n year = {2019},\n institution = {Lawrence Livermore National Laboratory},\n id = {afdd7fc2-7cf9-3d5d-b996-e7586c403693},\n created = {2021-05-31T23:08:10.281Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-05-31T23:08:10.281Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {margot},\n private_publication = {false},\n bibtype = {techreport},\n author = {Burton, G. C. and Campos, A. and Jang, I. and Kavouklis, C. and Stein, E.}\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{\n title = {Multiquantum Transitions in Oxygen and Nitrogen Molecules in Hypersonic Nonequilibrium Flows},\n type = {article},\n year = {2019},\n pages = {378-391},\n volume = {33},\n id = {222bf0d1-3d67-3c57-85b1-99ed93afcde9},\n created = {2021-07-11T21:26:39.951Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-07-11T21:26:39.951Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {josyula:jtht:2019},\n source_type = {article},\n private_publication = {false},\n bibtype = {article},\n author = {Josyula, Eswar and Suchyta, Casimir J and Vedula, Prakash and Burt, Jonathan M},\n doi = {10.2514/1.T5444},\n journal = {Journal of Thermophysics and Heat Transfer},\n number = {2}\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 National Center for Education Statistics, U.S. Department of Education, 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

@techreport{\n title = {Status and Trends in the Education of Racial and Ethnic Groups 2018},\n type = {techreport},\n year = {2019},\n issue = {NCES 2019-038},\n institution = {National Center for Education Statistics, U.S. Department of Education},\n id = {52e134bb-6361-3ac0-97ff-14790f580e10},\n created = {2021-07-23T19:28:31.509Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-07-23T19:28:31.509Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {nces:2019},\n source_type = {techreport},\n private_publication = {false},\n bibtype = {techreport},\n author = {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}

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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 \n\n\n\n
\n\n\n\n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\n \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{\n title = {Reattachment streaks in hypersonic compression ramp flow: an input–output analysis},\n type = {article},\n year = {2019},\n keywords = {compressible boundary layers,high-speed flow,transition to turbulence},\n pages = {113-135},\n volume = {880},\n publisher = {Cambridge University Press},\n id = {a2614819-f38c-3095-97f2-507ba3847647},\n created = {2021-10-25T22:54:14.837Z},\n accessed = {2021-10-25},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-10-25T22:55:56.286Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {dwivedi:jfm:2019},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Dwivedi, Anubhav and Sidharth, G. S. and Nichols, Joseph W. and Candler, Graham V. and Jovanović, Mihailo R.},\n doi = {10.1017/JFM.2019.702},\n journal = {Journal of Fluid Mechanics}\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 \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\n Journal of Sound and Vibration, 443: 74-89. 3 2019.\n \n\n\n\n
\n\n\n\n \n \n $\"Exploring$ 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

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@article{\n title = {Exploring the response of a thin, flexible panel to shock-turbulent boundary-layer interactions},\n type = {article},\n year = {2019},\n keywords = {Fluid-structure interaction,Shock boundary-layer interaction,Sonic fatigue},\n pages = {74-89},\n volume = {443},\n month = {3},\n publisher = {Academic Press},\n day = {17},\n id = {303595a5-52b1-38ae-b5fb-68d81f437cc1},\n created = {2021-10-28T19:50:39.385Z},\n accessed = {2021-10-28},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-10-28T19:50:40.015Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {spottswood:jsv:2019},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {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 doi = {10.1016/J.JSV.2018.11.035},\n journal = {Journal of Sound and Vibration}\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. 4 2019.\n \n\n\n\n
\n\n\n\n \n \n $\"Eigenvector$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\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{\n title = {Eigenvector perturbation methodology for uncertainty quantification of turbulence models},\n type = {article},\n year = {2019},\n pages = {044603},\n volume = {4},\n websites = {https://journals.aps.org/prfluids/abstract/10.1103/PhysRevFluids.4.044603},\n month = {4},\n publisher = {American Physical Society},\n day = {1},\n id = {2801f952-23bd-3b11-8a8d-6745bf78e811},\n created = {2022-01-15T17:07:08.315Z},\n accessed = {2022-01-15},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-01-15T17:07:08.315Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {thompson:prf:2019},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Thompson, Roney L. and Mishra, Aashwin Ananda and Iaccarino, Gianluca and Edeling, Wouter and Sampaio, Luiz},\n doi = {10.1103/PHYSREVFLUIDS.4.044603/FIGURES/9/MEDIUM},\n journal = {Physical Review Fluids},\n number = {4}\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 \n\n\n\n
\n\n\n\n \n \n $\"2019$ Website\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{\n title = {2019 Electron Transpiration Cooling of Materials},\n type = {misc},\n year = {2019},\n websites = {https://community.apan.org/wg/afosr/w/researchareas/25542/2019-electron-transpiration-cooling-of-materials/},\n city = {Washington, DC},\n id = {f042fca2-ae8d-360b-8edf-6e8c6c1cd79b},\n created = {2022-04-18T18:03:37.512Z},\n accessed = {2022-04-18},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-04-18T18:03:37.512Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {etc:workshop:2019},\n private_publication = {false},\n bibtype = {misc},\n author = {Birkan, Mitat and Sayi, Ali and Leyva, Ivett and Uribarri, Luke}\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. 5 2019.\n \n\n\n\n
\n\n\n\n \n \n $\"Study$ Paper\n \n \n \n $\"Study$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\n \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{\n title = {Study of the Effect of Electron Cooling: Overview of the Current State},\n type = {article},\n year = {2019},\n keywords = {Classical and Continuum Physics},\n pages = {287-292},\n volume = {64},\n websites = {https://link.springer.com/article/10.1134/S106378421903006X},\n month = {5},\n publisher = {Springer},\n day = {15},\n id = {cf851ae3-5d5d-3768-93f2-bb99717738f1},\n created = {2022-04-18T18:32:19.504Z},\n accessed = {2022-04-18},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-04-18T18:32:20.085Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {bezverkhnii:tp:2019},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Bezverkhnii, N. O. and Bobashev, S. V. and Kolychev, A. V. and Monakhov, N. A. and Ponyaev, S. A. and Sakharov, V. A.},\n doi = {10.1134/S106378421903006X},\n journal = {Technical Physics 2019 64:3},\n number = {3}\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 \n Computational predictions of the hypersonic material environmental test system arcjet facility.\n \n \n \n \n\n\n \n\n\n\n Journal of Thermophysics and Heat Transfer, 33(1): 199-209. 9 2019.\n \n\n\n\n
\n\n\n\n \n \n $\"Computational$ 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 \n \n \n \n \n\n\n\n

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@article{\n title = {Computational predictions of the hypersonic material environmental test system arcjet facility},\n type = {article},\n year = {2019},\n keywords = {Catalysis,Enthalpy,Heat Flux,Hypersonic Vehicles,Molecular Tagging Velocimetry,NASA Langley Research Center,Numerical Simulation,Slug Calorimeters,Stagnation Temperature,Thermal Protection System},\n pages = {199-209},\n volume = {33},\n month = {9},\n publisher = {American Institute of Aeronautics and Astronautics Inc.},\n day = {14},\n id = {bbef1414-1ec0-3217-a83f-34ed6884ffed},\n created = {2022-04-18T23:17:08.626Z},\n accessed = {2022-04-18},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-04-18T23:18:09.658Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {brune:jtht:2019},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Brune, Andrew J. and Bruce, Walter E. and Glass, David E. and Splinter, Scott C.},\n doi = {10.2514/1.T5490/ASSET/IMAGES/LARGE/FIGURE15.JPEG},\n journal = {Journal of Thermophysics and Heat Transfer},\n number = {1}\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 AIAA Scitech 2019 Forum, 2019. American Institute of Aeronautics and Astronautics Inc, AIAA\n \n\n\n\n
\n\n\n\n \n \n $\"A$ Paper\n \n \n \n $\"A$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\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{\n title = {A chemical equilibrium analysis approach to oxidation and nitridation of silicon carbide},\n type = {inproceedings},\n year = {2019},\n websites = {https://arc.aiaa.org/doi/10.2514/6.2019-0243},\n publisher = {American Institute of Aeronautics and Astronautics Inc, AIAA},\n id = {7bf33548-cec5-3b4a-a139-e12cd92b2bbe},\n created = {2022-06-07T19:17:32.607Z},\n accessed = {2022-06-07},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-06-07T19:17:33.476Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {chen:scitech:2019},\n private_publication = {false},\n abstract = {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 bibtype = {inproceedings},\n author = {Chen, Samuel Y. and Boyd, Iain D.},\n doi = {10.2514/6.2019-0243},\n booktitle = {AIAA Scitech 2019 Forum}\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 \n Shape Optimization of Reentry Vehicles to Minimize Heat Loading.\n \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 $\"Shape$ Paper\n \n \n \n $\"Shape$ Website\n \n \n\n \n \n doi\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{\n title = {Shape Optimization of Reentry Vehicles to Minimize Heat Loading},\n type = {article},\n year = {2019},\n pages = {785-796},\n volume = {33},\n websites = {https://arc.aiaa.org/doi/10.2514/1.T5705},\n publisher = {American Institute of Aeronautics and Astronautics Inc.},\n id = {4917932d-d736-3b8c-adb4-5adf6984b7b7},\n created = {2022-06-16T16:33:28.731Z},\n accessed = {2021-01-04},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-09-25T21:43:26.843Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {eyi:jtht:2019a},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Eyi, Sinan and Hanquist, Kyle M. and Boyd, Iain D.},\n doi = {10.2514/1.T5705},\n journal = {Journal of Thermophysics and Heat Transfer},\n number = {3},\n keywords = {thermal}\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). 6 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

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@article{\n title = {Lagrangian diffusive reactor for detailed thermochemical computations of plasma flows},\n type = {article},\n year = {2019},\n keywords = {Lagrangian chemical reactor,Nonequilibrium plasmas,chemically reactive flows,rarefied gas dynamics},\n volume = {28},\n month = {6},\n publisher = {IOP Publishing},\n day = {3},\n id = {87a7a84b-2048-36ba-a7df-62bc42f5510c},\n created = {2022-09-16T23:02:25.937Z},\n accessed = {2022-09-16},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-09-16T23:02:25.937Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {boccelli:psst:2019},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Boccelli, Stefano and Bariselli, Federico and Dias, Bruno and Magin, Thierry E.},\n doi = {10.1088/1361-6595/AB09B5},\n journal = {Plasma Sources Science and Technology},\n number = {6}\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 Vibrational energy transfer and collision-induced dissociation in O + O2 collisions.\n \n \n \n\n\n \n\n\n\n Journal of Thermophysics and Heat Transfer, 33(3): 797-807. 2 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 \n \n \n \n \n \n \n \n\n\n\n

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@article{\n title = {Vibrational energy transfer and collision-induced dissociation in O + O2 collisions},\n type = {article},\n year = {2019},\n keywords = {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 pages = {797-807},\n volume = {33},\n month = {2},\n publisher = {American Institute of Aeronautics and Astronautics Inc.},\n day = {19},\n id = {3812f441-494f-3e75-97d5-31d248f84946},\n created = {2022-09-19T20:25:22.837Z},\n accessed = {2022-09-19},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-09-26T19:17:27.263Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {grover:jtht:2019},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Grover, Maninder S. and Schwartzentruber, Thomas E. and Varga, Zoltan and Truhlar, Donald G.},\n doi = {10.2514/1.T5551},\n journal = {Journal of Thermophysics and Heat Transfer},\n number = {3}\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 Ph.D. Thesis, 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

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@phdthesis{\n title = {Aero-Optical Assessments of Hypersonic Flowfields},\n type = {phdthesis},\n year = {2019},\n institution = {University of Michigan},\n id = {fbb05765-4636-32dc-9c65-edb9a33280f0},\n created = {2022-11-17T04:19:43.821Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-11-17T04:19:43.821Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {mackey:thesis:2019},\n source_type = {phdthesis},\n private_publication = {false},\n bibtype = {phdthesis},\n author = {Mackey, Lauren E}\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 \n Direct simulation Monte Carlo on petaflop supercomputers and beyond.\n \n \n \n \n\n\n \n\n\n\n Physics of Fluids, 31(8): 086101. 8 2019.\n \n\n\n\n
\n\n\n\n \n \n $\"Direct$ 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

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@article{\n title = {Direct simulation Monte Carlo on petaflop supercomputers and beyond},\n type = {article},\n year = {2019},\n keywords = {Monte Carlo methods,flow simulation,rarefied fluid dynamics},\n pages = {086101},\n volume = {31},\n month = {8},\n publisher = {AIP Publishing LLCAIP Publishing},\n day = {1},\n id = {175a1606-af38-3b8f-80be-cc0e01d70670},\n created = {2022-11-17T18:15:21.828Z},\n accessed = {2022-11-17},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-11-17T18:15:22.434Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {plimpton:pof:2019},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {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 doi = {10.1063/1.5108534},\n journal = {Physics of Fluids},\n number = {8}\n}

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\n \n 2018\n \n \n (18)\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 \n Effectiveness of Thermionic Emission for Cooling Hypersonic Vehicle Surfaces.\n \n \n \n \n\n\n \n\n\n\n In AIAA Aerospace Sciences Meeting, 2018, 2018. AIAA Paper 2018-1714\n \n\n\n\n
\n\n\n\n \n \n $\"Effectiveness$ 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

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@inproceedings{\n title = {Effectiveness of Thermionic Emission for Cooling Hypersonic Vehicle Surfaces},\n type = {inproceedings},\n year = {2018},\n publisher = {AIAA Paper 2018-1714},\n city = {Kissimmee, F},\n id = {085fd2c1-e955-39eb-ab8c-738671bc7c04},\n created = {2021-01-05T20:43:34.967Z},\n accessed = {2021-01-04},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-01-05T20:43:41.653Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {hanquist:scitech:2018},\n source_type = {inproceedings},\n private_publication = {false},\n abstract = {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 bibtype = {inproceedings},\n author = {Hanquist, Kyle M. and Boyd, Iain D.},\n doi = {10.2514/6.2018-1714},\n booktitle = {AIAA Aerospace Sciences Meeting, 2018},\n keywords = {etc}\n}

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\n \n\n \n \n Hara, K.; and Hanquist, K., M.\n\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\n Plasma Sources Science and Technology, 27(6): 65004. 2018.\n \n\n\n\n
\n\n\n\n \n \n $\"Test$ 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 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

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@article{\n title = {Test cases for grid-based direct kinetic modeling of plasma flows},\n type = {article},\n year = {2018},\n keywords = {etc,own,plasma},\n pages = {65004},\n volume = {27},\n publisher = {Institute of Physics Publishing},\n id = {2458a33c-4889-3c59-86f8-5fc9af79d122},\n created = {2021-01-05T20:43:34.968Z},\n accessed = {2021-01-04},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-09-25T21:50:27.064Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {hara:psst:2018},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Hara, Kentaro and Hanquist, Kyle M.},\n doi = {10.1088/1361-6595/aac6b9},\n journal = {Plasma Sources Science and Technology},\n number = {6}\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 \n Aerothermodynamic Design Optimization of Hypersonic Vehicles.\n \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 $\"Aerothermodynamic$ 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

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@inproceedings{\n title = {Aerothermodynamic Design Optimization of Hypersonic Vehicles},\n type = {inproceedings},\n year = {2018},\n publisher = {AIAA Paper 2018-3108},\n city = {Atlanta, GA},\n id = {912786f7-b5f2-3fea-805e-b87e5656b94b},\n created = {2021-01-05T20:43:35.489Z},\n accessed = {2021-01-04},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-01-05T20:43:54.272Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {eyi:aviation:2018},\n source_type = {inproceedings},\n private_publication = {false},\n abstract = {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 bibtype = {inproceedings},\n author = {Eyi, Sinan and Hanquist, Kyle M. and Boyd, Iain D.},\n doi = {10.2514/6.2018-3108},\n booktitle = {2018 Multidisciplinary Analysis and Optimization Conference}\n}

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\n \n\n \n \n Hanquist, K., M.; and Boyd, I., D.\n\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\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 $\"Modeling$ 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

@inproceedings{\n title = {Modeling of Excited Oxygen in Post Normal Shock Waves},\n type = {inproceedings},\n year = {2018},\n publisher = {AIAA Paper 2018-3769},\n city = {Atlanta, GA},\n id = {93383212-16cf-30d9-a290-4f56682ca798},\n created = {2021-01-05T20:43:35.506Z},\n accessed = {2021-01-04},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-01-05T20:43:55.835Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {hanquist:aviation:18},\n source_type = {inproceedings},\n private_publication = {false},\n abstract = {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 bibtype = {inproceedings},\n author = {Hanquist, Kyle M. and Boyd, Iain D.},\n doi = {10.2514/6.2018-3769},\n booktitle = {2018 Joint Thermophysics and Heat Transfer Conference}\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

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@article{\n title = {The Quest to Conquer the Space Junk Problem},\n type = {article},\n year = {2018},\n volume = {561},\n id = {56b5918d-8045-3e2d-804e-8ea3e80a2fc3},\n created = {2021-03-05T21:31:54.673Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-03-05T21:31:54.673Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {witze:nature:2018},\n private_publication = {false},\n bibtype = {article},\n author = {Witze, Alexandra},\n journal = {Nature}\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 AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, 2018, 2018. American Institute of Aeronautics and Astronautics Inc, AIAA\n \n\n\n\n
\n\n\n\n \n \n $\"An$ Paper\n \n \n \n $\"An$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\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{\n title = {An examination of vehicle design tradeoffs and trajectory optimization for trimmed scramjet-powered hypersonic vehicles on ascent},\n type = {inproceedings},\n year = {2018},\n issue = {210049},\n websites = {https://arc.aiaa.org/doi/abs/10.2514/6.2018-0417},\n publisher = {American Institute of Aeronautics and Astronautics Inc, AIAA},\n id = {616d777b-6b0b-3844-9e55-3cfbf1358663},\n created = {2021-05-29T00:09:06.103Z},\n accessed = {2021-05-28},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-05-29T00:09:45.855Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {mbagwu:aiaa:2018},\n private_publication = {false},\n abstract = {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 bibtype = {inproceedings},\n author = {Mbagwu, Chukwuka C. and Driscoll, James F.},\n doi = {10.2514/6.2018-0417},\n booktitle = {AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, 2018}\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 2018 Plasmadynamics and Lasers Conference, 6 2018. AIAA 2018-3904\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{\n title = {Aero-optical effects in non-equilibrium air},\n type = {inproceedings},\n year = {2018},\n month = {6},\n publisher = {AIAA 2018-3904},\n city = {Atlanta, Georgia},\n id = {a66e5c85-1106-3adf-a217-7137f6a87d3d},\n created = {2021-05-31T19:42:51.830Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-05-31T19:42:51.830Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {tropina:plc:2018},\n source_type = {inproceedings},\n private_publication = {false},\n bibtype = {inproceedings},\n author = {Tropina, Albina and Wu, Yue and Limbach, Christopher and Miles, Richard B},\n booktitle = {2018 Plasmadynamics and Lasers Conference}\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 Fluid Dynamics Conference, 2018. American Institute of Aeronautics and Astronautics Inc, AIAA\n \n\n\n\n
\n\n\n\n \n \n $\"Turbulent$ 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

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@inproceedings{\n title = {Turbulent hypersonic flow effects on optical sensor performance},\n type = {inproceedings},\n year = {2018},\n publisher = {American Institute of Aeronautics and Astronautics Inc, AIAA},\n id = {4bbcd83c-0927-3b06-9bd4-af47aa56428d},\n created = {2021-05-31T22:48:55.033Z},\n accessed = {2021-05-31},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-07-12T10:41:10.629Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {mackey:aviation:2018},\n private_publication = {false},\n abstract = {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 bibtype = {inproceedings},\n author = {Mackey, Lauren E. and Boyd, Iain D. and Jewell, Joseph S. and Leger, Timothy J.},\n doi = {10.2514/6.2018-3712},\n booktitle = {2018 Fluid Dynamics Conference}\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. 1 2018.\n \n\n\n\n
\n\n\n\n \n \n $\"Thermochemical$ Paper\n \n \n \n $\"Thermochemical$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\n \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{\n title = {Thermochemical nonequilibrium parameter modification of oxygen for a two-temperature model},\n type = {article},\n year = {2018},\n keywords = {oxygen,pipe flow,rotational-vibrational states,shock tubes,shock waves,thermochemistry},\n pages = {016101},\n volume = {30},\n websites = {https://aip.scitation.org/doi/abs/10.1063/1.4996799},\n month = {1},\n publisher = {AIP Publishing LLCAIP Publishing},\n day = {2},\n id = {b27b3090-8906-327f-9233-99efc451a31c},\n created = {2021-07-11T21:04:30.732Z},\n accessed = {2021-07-11},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-07-11T21:05:22.841Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {kim:pof:2018},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Kim, Jae Gang and Park, Gisu},\n doi = {10.1063/1.4996799},\n journal = {Physics of Fluids},\n number = {1}\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 AIAA Aerospace Sciences Meeting, 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

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@inproceedings{\n title = {Large Eddy Simulation of Boundary Layer Transition Induced by DBD Plasma Actuators},\n type = {inproceedings},\n year = {2018},\n id = {055800a8-47cb-351a-b8aa-3ee72ea07eae},\n created = {2021-07-11T22:06:03.557Z},\n accessed = {2021-07-11},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-07-11T22:06:03.557Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {parent:scitech:2018},\n private_publication = {false},\n abstract = {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 bibtype = {inproceedings},\n author = {Parent, Bernard and Shneider, Mikhail N and Macheret, Sergey O},\n doi = {10.2514/6.2018-0444},\n booktitle = {AIAA Aerospace Sciences Meeting}\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 O2-N2 collisions at hypersonic temperatures.\n \n \n \n\n\n \n\n\n\n In AIAA Aviation and Aeronautics Forum and Exposition, 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{\n title = {Kinetics of O2-N2 collisions at hypersonic temperatures},\n type = {inproceedings},\n year = {2018},\n publisher = {AIAA Paper 2018-3438},\n city = {Atlanta, GA},\n id = {f8075fe5-cd67-3d1e-8957-bc174bf87a11},\n created = {2021-07-12T08:09:32.327Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-09-26T19:12:11.024Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {andrienko:aviation:2018},\n source_type = {inproceedings},\n private_publication = {false},\n bibtype = {inproceedings},\n author = {Andrienko, Daniil A and Boyd, Iain D},\n booktitle = {AIAA Aviation and Aeronautics Forum and Exposition}\n}

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\n \n\n \n \n Campanell, M., D.\n\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\n Physical Review E, 97: 1-16. 2018.\n \n\n\n\n
\n\n\n\n \n \n $\"Alternative$ 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

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@article{\n title = {Alternative model of space-charge-limited thermionic current flow through a plasma},\n type = {article},\n year = {2018},\n keywords = {doi:10.1103/PhysRevE.97.043207 url:https://doi.org},\n pages = {1-16},\n volume = {97},\n id = {56e511c5-2b5c-3ffa-9e29-e8b0a8b4bdbd},\n created = {2021-07-19T20:57:24.018Z},\n accessed = {2021-07-19},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-07-19T20:57:34.065Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {campanell:prf:2018},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Campanell, M D},\n doi = {10.1103/PhysRevE.97.043207},\n journal = {Physical Review E}\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 AIAA SPACE Forum, 2018. \n \n\n\n\n
\n\n\n\n \n \n $\"Influence$ Paper\n \n \n \n $\"Influence$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\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{\n title = {Influence of hypersonic fluid-structure interaction on the control authority of a trailing-edge flap},\n type = {inproceedings},\n year = {2018},\n websites = {http://arc.aiaa.org},\n id = {921e48be-92c3-38c2-b50a-e3e69baf898e},\n created = {2021-10-26T22:18:45.036Z},\n accessed = {2021-10-26},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-10-26T22:18:45.644Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {bhattrai:space:2018},\n private_publication = {false},\n abstract = {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 bibtype = {inproceedings},\n author = {Bhattrai, Sudip and Mcquellin, Liam P and Currao, Gaetano M D and Neely, Andrew J and Buttsworth, David R},\n doi = {10.2514/6.2018-5265},\n booktitle = {AIAA SPACE Forum}\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 \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\n IEEE Control Systems, 38(3): 63-86. 6 2018.\n \n\n\n\n
\n\n\n\n \n \n $\"Data-Driven$ 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

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@article{\n title = {Data-Driven Sparse Sensor Placement for Reconstruction: Demonstrating the Benefits of Exploiting Known Patterns},\n type = {article},\n year = {2018},\n pages = {63-86},\n volume = {38},\n month = {6},\n publisher = {Institute of Electrical and Electronics Engineers Inc.},\n day = {1},\n id = {b113503f-cf63-3da0-a2ab-30c1d965e251},\n created = {2021-11-06T18:18:01.207Z},\n accessed = {2021-11-06},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-11-06T18:18:03.974Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {manohar:ieee:2018},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Manohar, Krithika and Brunton, Bingni W. and Kutz, J. Nathan and Brunton, Steven L.},\n doi = {10.1109/MCS.2018.2810460},\n journal = {IEEE Control Systems},\n number = {3}\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. 9 2018.\n \n\n\n\n
\n\n\n\n \n \n $\"Comparison$ Paper\n \n \n \n $\"Comparison$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\n \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{\n title = {Comparison of potential energy surface and computed rate coefficients for N2 dissociation},\n type = {article},\n year = {2018},\n keywords = {Aerothermodynamics,CFD,Classical Mechanics,Computing,Direct Simulation Monte Carlo,Energy Distribution,NASA Ames Research Center,Schrodinger Equation,Shock Tube,Thermal Nonequilibrium},\n pages = {869-881},\n volume = {32},\n websites = {https://arc.aiaa.org/doi/abs/10.2514/1.T5417},\n month = {9},\n publisher = {American Institute of Aeronautics and Astronautics Inc.},\n day = {25},\n id = {c060f56b-abcd-3596-b33c-a652c02ed330},\n created = {2021-12-10T19:37:14.020Z},\n accessed = {2021-12-10},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-12-10T19:37:14.737Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {jaffe:jtht:2008},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Jaffe, Richard L. and Grover, Maninder and Venturi, Simone and Schwenke, David W. and Valentini, Paolo and Schwartzentruber, Thomas E. and Panesi, Marco},\n doi = {10.2514/1.T5417},\n journal = {Journal of Thermophysics and Heat Transfer},\n number = {4}\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 Ph.D. Thesis, 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

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@phdthesis{\n title = {Modeling and Analysis of Chemical Kinetics for Hypersonic Flows in Air},\n type = {phdthesis},\n year = {2018},\n institution = {University of Minnesota},\n id = {e6866350-b7c0-38e2-bf15-7f6669f31f08},\n created = {2021-12-10T19:49:28.400Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-12-10T19:49:28.400Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {chaudhry:thesis:2018},\n source_type = {phdthesis},\n private_publication = {false},\n bibtype = {phdthesis},\n author = {Chaudhry, Ross S}\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. 10 2018.\n \n\n\n\n
\n\n\n\n \n \n $\"Surface$ Paper\n \n \n \n $\"Surface$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\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{\n title = {Surface recombination in the direct simulation Monte Carlo method},\n type = {article},\n year = {2018},\n pages = {107105},\n volume = {30},\n websites = {https://aip.scitation.org/doi/abs/10.1063/1.5048353},\n month = {10},\n publisher = {AIP Publishing LLCAIP Publishing},\n day = {31},\n id = {2903681d-7ab5-3fc9-b49b-10a393d43e5a},\n created = {2022-06-09T14:34:22.935Z},\n accessed = {2022-06-09},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-06-09T14:34:23.754Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {molchanova:pof:2018},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Molchanova, Alexandra N. and Kashkovsky, Alexander V. and Bondar, Yevgeniy A.},\n doi = {10.1063/1.5048353},\n journal = {Physics of Fluids},\n number = {10}\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. 9 2018.\n \n\n\n\n
\n\n\n\n \n \n $\"Quasiclassical$ 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 \n \n \n \n \n\n\n\n

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@article{\n title = {Quasiclassical trajectory analysis of nitrogen for high-temperature chemical kinetics},\n type = {article},\n year = {2018},\n keywords = {Boltzmann Constant,Born Oppenheimer Approximation,CFD,Energy Distribution,High Temperature Chemical Kinetics,Hypersonic Flows,Internal Energy,Probability Density Functions,Shock Tube,Thermal Nonequilibrium},\n pages = {833-845},\n volume = {32},\n month = {9},\n publisher = {American Institute of Aeronautics and Astronautics Inc.},\n day = {25},\n id = {1c82d1a0-7f97-3c91-8358-edd4ed90f177},\n created = {2022-09-16T20:12:57.439Z},\n accessed = {2022-09-16},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-09-26T19:15:44.350Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {chaudhry:jtht:2018},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Chaudhry, Ross S. and Bender, Jason D. and Schwartzentruber, Thomas E. and Candler, Graham V.},\n doi = {10.2514/1.T5484},\n journal = {Journal of Thermophysics and Heat Transfer},\n number = {4}\n}

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\n \n 2017\n \n \n (22)\n \n \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 \n Evaluation of Computational Modeling of Electron Transpiration Cooling at High Enthalpies.\n \n \n \n \n\n\n \n\n\n\n Journal of Thermophysics and Heat Transfer, 31(2): 283-293. 4 2017.\n \n\n\n\n
\n\n\n\n \n \n $\"Evaluation$ 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 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{\n title = {Evaluation of Computational Modeling of Electron Transpiration Cooling at High Enthalpies},\n type = {article},\n year = {2017},\n pages = {283-293},\n volume = {31},\n month = {4},\n publisher = {American Institute of Aeronautics and Astronautics Inc.},\n day = {26},\n id = {2d923798-40a6-3811-a986-ed0476a195da},\n created = {2021-01-05T20:43:34.906Z},\n accessed = {2021-01-04},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-12-28T16:46:16.995Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {hanquist:jtht:2017},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Hanquist, Kyle M. and Alkandry, Hicham and Boyd, Iain D.},\n doi = {10.2514/1.T4932},\n journal = {Journal of Thermophysics and Heat Transfer},\n number = {2},\n keywords = {etc}\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 \n Detailed modeling of electron emission for transpiration cooling of hypersonic vehicles.\n \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 $\"Detailed$ 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 2 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{\n title = {Detailed modeling of electron emission for transpiration cooling of hypersonic vehicles},\n type = {article},\n year = {2017},\n keywords = {etc,plasma},\n pages = {1-13},\n volume = {121},\n publisher = {American Institute of Physics Inc.},\n id = {3121179a-fd3a-37ff-8d93-12f45276c346},\n created = {2021-01-05T20:43:35.166Z},\n accessed = {2021-01-04},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-09-25T21:50:42.393Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {hanquist:jap:2017},\n private_publication = {false},\n abstract = {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 (CFD) can be used to investigate the feasibility of ETC in a hypersonic environment. A modeling approach is presented for ETC, which includes developing the boundary conditions for electron emission from the surface, accounting for the space-charge limit effects of the near-wall plasma sheath. The space-charge limit models are assessed using 1D direct-kinetic plasma sheath simulations, taking into account the thermionically emitted electrons from the surface. The simulations agree well with the space-charge limit theory proposed by Takamura et al. for emitted electrons with a finite temperature, especially at low values of wall bias, which validates the use of the theoretical model for the hypersonic CFD code. The CFD code with the analytical sheath models is then used for a test case typical of a leading edge radius in a hypersonic flight environment. The CFD results show that ETC can lower the surface temperature of sharp leading edges of hypersonic vehicles, especially at higher velocities, due to the increase in ionized species enabling higher electron heat extraction from the surface. The CFD results also show that space-charge limit effects can limit the ETC reduction of surface temperatures, in comparison to thermionic emission assuming no effects of the electric field within the sheath.},\n bibtype = {article},\n author = {Hanquist, Kyle M. and Hara, Kentaro and Boyd, Iain D.},\n doi = {10.1063/1.4974961},\n journal = {Journal of Applied Physics},\n number = {5}\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, 2017.\n \n\n\n\n
\n\n\n\n \n \n $\"Modeling$ Website\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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@phdthesis{\n title = {Modeling of Electron Transpiration Cooling for Leading Edges of Hypersonic Vehicles},\n type = {phdthesis},\n year = {2017},\n keywords = {etc},\n websites = {http://hdl.handle.net/2027.42/138537},\n city = {Ann Arbor},\n institution = {University of Michigan},\n id = {74ed45f8-9709-3985-9702-9b3e12e3cdc3},\n created = {2021-01-05T20:43:35.301Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-12-28T16:39:17.534Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {hanquist:thesis:2017},\n source_type = {phdthesis},\n private_publication = {false},\n bibtype = {phdthesis},\n author = {Hanquist, Kyle M}\n}

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\n \n\n \n \n Hanquist, K., M.; and Boyd, I., D.\n\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\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 $\"Computational$ Website\n \n \n\n \n \n doi\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{\n title = {Computational analysis of electron transpiration cooling for hypersonic vehicles},\n type = {inproceedings},\n year = {2017},\n pages = {1-12},\n websites = {https://arc.aiaa.org/doi/abs/10.2514/6.2017-0900},\n publisher = {AIAA Paper 2017-0900},\n city = {Grapevine, TX},\n id = {3030a5d4-33c1-32c1-82f0-e118eb349278},\n created = {2021-01-05T20:43:35.305Z},\n accessed = {2021-01-04},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-01-05T20:43:35.305Z},\n read = {false},\n starred = {true},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {hanquist:scitech:2017},\n source_type = {inproceedings},\n private_publication = {false},\n abstract = {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 bibtype = {inproceedings},\n author = {Hanquist, Kyle M. and Boyd, Iain D.},\n doi = {10.2514/6.2017-0900},\n booktitle = {AIAA SciTech Forum - 55th AIAA Aerospace Sciences Meeting},\n keywords = {etc}\n}

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\n \n\n \n \n Neitzel, K., J.; and Hanquist, K., M.\n\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\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 $\"Aerodynamic$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\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{\n title = {Aerodynamic optimization of a golf driver using computational fluid dynamics},\n type = {inproceedings},\n year = {2017},\n pages = {1-8},\n websites = {https://arc.aiaa.org/doi/abs/10.2514/6.2017-0724},\n publisher = {AIAA Paper 2017-0724},\n city = {Grapevine, TX},\n id = {8e425398-ea11-3db9-9f3a-d385c39ed24e},\n created = {2021-01-05T20:43:35.690Z},\n accessed = {2021-01-04},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-01-05T20:43:35.690Z},\n read = {false},\n starred = {true},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {neitzel:scitech:2017},\n source_type = {inproceedings},\n private_publication = {false},\n abstract = {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 bibtype = {inproceedings},\n author = {Neitzel, Kevin J. and Hanquist, Kyle M.},\n doi = {10.2514/6.2017-0724},\n booktitle = {AIAA SciTech Forum - 55th AIAA Aerospace Sciences Meeting}\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 AIAA Scitech 2017 Forum, 2017. \n \n\n\n\n
\n\n\n\n \n \n $\"Comparisons$ Paper\n \n \n \n $\"Comparisons$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\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{\n title = {Comparisons of Measured and Modeled Aero-thermal Distributions for Complex Hypersonic Configurations},\n type = {inproceedings},\n year = {2017},\n websites = {http://arc.aiaa.org},\n city = {Grapevine, TX},\n id = {ab716a52-6d79-345e-8a05-89e2a801ed04},\n created = {2021-02-17T23:27:14.843Z},\n accessed = {2021-02-17},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-02-17T23:27:18.256Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {sagerman:aiaa:2017},\n private_publication = {false},\n abstract = {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 bibtype = {inproceedings},\n author = {Sagerman, Denton G and Dasque, Nastassja and Rumpfkeil, Markus P and Hellman, Barry},\n doi = {10.2514/6.2017-0264},\n booktitle = {AIAA Scitech 2017 Forum}\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 \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\n J. Astron. Space Sci, 34(4): 289-302. 2017.\n \n\n\n\n
\n\n\n\n \n \n $\"A$ 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

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@article{\n title = {A Study on Re-entry Predictions of Uncontrolled Space Objects for Space Situational Awareness},\n type = {article},\n year = {2017},\n keywords = {re-entry prediction,space situational awareness,uncontrolled space objects},\n pages = {289-302},\n volume = {34},\n id = {812bc3b1-6b53-350f-b503-fe76b0932eff},\n created = {2021-03-05T23:41:34.635Z},\n accessed = {2021-03-05},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-03-05T23:41:38.917Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {choi:jass:2017},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Choi, Eun-Jung and Cho, Sungki and Lee, Deok-Jin and Kim, Siwoo and Hyun Jo, Jung},\n doi = {10.5140/JASS.2017.34.4.289},\n journal = {J. Astron. Space Sci},\n number = {4}\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, 1. 2017.\n \n\n\n\n
\n\n\n\n \n \n $\"Turbine$ 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\n \n \n \n \n \n \n \n\n \n \n \n \n \n \n \n \n \n\n\n\n

\n

@article{\n title = {Turbine blade tip aero-thermal management: Some recent advances and research outlook},\n type = {article},\n year = {2017},\n keywords = {aerodynamics,gas turbine,heat transfer},\n volume = {1},\n id = {6cc8aa5f-ca3a-3220-ba20-12dbffcdc235},\n created = {2021-04-21T23:27:49.315Z},\n accessed = {2021-04-21},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-07-23T21:07:17.335Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {zhang:jgpps:2017},\n private_publication = {false},\n bibtype = {article},\n author = {Zhang, Qiang and He, Li},\n doi = {10.22261/JGPPS.K7ADQC},\n journal = {Journal of the Global Power and Propulsion Society}\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

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@article{\n title = {Aerothermochemical Nonequilibrium Modeling for Oxygen Flows},\n type = {article},\n year = {2017},\n pages = {634-645},\n volume = {31},\n id = {26ab2a49-dc05-317e-bf3c-9ec8c3230d9b},\n created = {2021-07-11T20:34:38.321Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-07-11T20:34:38.321Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {neitzel:jtht:2017},\n source_type = {article},\n private_publication = {false},\n bibtype = {article},\n author = {Neitzel, K J and Andrienko, D A and Boyd, I D},\n journal = {Journal of Thermophysics and Heat Transfer},\n number = {3}\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 \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\n Frontiers in Mechanical Engineering. 11 2017.\n \n\n\n\n
\n\n\n\n \n \n $\"Thermionic$ 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

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@article{\n title = {Thermionic Energy Conversion in the Twenty-first Century: Advances and Opportunities for Space and Terrestrial Applications},\n type = {article},\n year = {2017},\n keywords = {Photo-Enhanced Thermionic Emission,Thermal energy conversion,Thermionic energy conversion,thermionic emission,thermoelectronic energy conversion},\n month = {11},\n publisher = {Frontiers},\n day = {8},\n id = {d732560a-1959-3eaa-b7a1-e0b42c607817},\n created = {2021-07-20T04:45:07.268Z},\n accessed = {2021-07-19},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-07-20T04:45:14.992Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {go:fme:2017},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Go, David B. and Haase, John R. and George, Jeffrey and Mannhart, Jochen and Wanke, Robin and Nojeh, Alireza and Nemanich, Robert},\n doi = {10.3389/FMECH.2017.00013},\n journal = {Frontiers in Mechanical Engineering}\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 The von Karman Institute for Fluid Dynamics, 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\n

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@techreport{\n title = {Plasma Wind Tunnel Testing of Electron Transpiration Cooling Concept},\n type = {techreport},\n year = {2017},\n keywords = {etc},\n issue = {AD1028658},\n institution = {The von Karman Institute for Fluid Dynamics},\n id = {2acda023-69a6-3de0-9ed9-3c38b3c77eed},\n created = {2021-07-22T16:18:55.208Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-07-22T16:18:55.208Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {chazot:etc:2017},\n source_type = {techreport},\n private_publication = {false},\n bibtype = {techreport},\n author = {Chazot, Olivier and Helber, Bernd}\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). 10 2017.\n \n\n\n\n
\n\n\n\n \n \n $\"Improving$ 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

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@article{\n title = {Improving Underrepresented Minority Student Persistence in STEM},\n type = {article},\n year = {2017},\n volume = {15},\n month = {10},\n publisher = {American Society for Cell Biology},\n day = {13},\n id = {26fcbc63-d6db-32da-ae6d-888b57309308},\n created = {2021-07-23T20:49:27.400Z},\n accessed = {2021-07-23},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-07-23T21:07:17.129Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {estrada:cbe:2017},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {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 doi = {10.1187/CBE.16-01-0038},\n journal = {CBE - Life Sciences Education},\n number = {3}\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 \n Multi-fidelity Gaussian process regression for prediction of random fields.\n \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 $\"Multi-fidelity$ 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

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@article{\n title = {Multi-fidelity Gaussian process regression for prediction of random fields},\n type = {article},\n year = {2017},\n keywords = {Gaussian random fields,Multi-fidelity modeling,Recursive co-kriging,Uncertainty quantification},\n pages = {36-50},\n volume = {336},\n day = {1},\n id = {d41f5c44-5345-31c2-b6d9-b0b405d9924d},\n created = {2021-10-26T04:25:11.366Z},\n accessed = {2021-01-12},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-10-26T04:25:12.110Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {parussini:jcp:2017},\n private_publication = {false},\n abstract = {We propose a new multi-fidelity Gaussian process regression (GPR) approach for prediction of random fields based on observations of surrogate models or hierarchies of surrogate models. Our method builds upon recent work on recursive Bayesian techniques, in particular recursive co-kriging, and extends it to vector-valued fields and various types of covariances, including separable and non-separable ones. The framework we propose is general and can be used to perform uncertainty propagation and quantification in model-based simulations, multi-fidelity data fusion, and surrogate-based optimization. We demonstrate the effectiveness of the proposed recursive GPR techniques through various examples. Specifically, we study the stochastic Burgers equation and the stochastic Oberbeck–Boussinesq equations describing natural convection within a square enclosure. In both cases we find that the standard deviation of the Gaussian predictors as well as the absolute errors relative to benchmark stochastic solutions are very small, suggesting that the proposed multi-fidelity GPR approaches can yield highly accurate results.},\n bibtype = {article},\n author = {Parussini, L. and Venturi, D. and Perdikaris, P. and Karniadakis, G. E.},\n doi = {10.1016/j.jcp.2017.01.047},\n journal = {Journal of Computational Physics}\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 7th European Conference for Aeronautics and Space Sciences (EUCASS), 2017. \n \n\n\n\n
\n\n\n\n \n \n $\"Hypersonic$ Paper\n \n \n \n $\"Hypersonic$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\n \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{\n title = {Hypersonic Fluid-Structure Interaction on a Cantilevered Plate},\n type = {inproceedings},\n year = {2017},\n websites = {https://www.researchgate.net/publication/320087702},\n id = {927afa35-2ba5-35ce-8285-c1e9694bd466},\n created = {2021-10-26T22:11:07.288Z},\n accessed = {2021-10-26},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-10-26T22:11:07.874Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {currao:eucass:2017},\n private_publication = {false},\n abstract = {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 bibtype = {inproceedings},\n author = {Currao, Gaetano and Neely, Andrew and Robert Buttsworth, David and Gai, S.},\n doi = {10.13009/EUCASS2017-299},\n booktitle = {7th European Conference for Aeronautics and Space Sciences (EUCASS)}\n}

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\n\n\n

\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 Andrienko, D., A.; and Boyd, I., D.\n\n\n \n \n \n \n State-specific dissociation in O2-O2 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 \n link\n \n \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{\n title = {State-specific dissociation in O2-O2 collisions by quasiclassical trajectory method},\n type = {article},\n year = {2017},\n pages = {74-81},\n volume = {491},\n id = {3128bf47-ecbc-358b-9aee-0818e6149d0a},\n created = {2021-12-10T18:33:10.536Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-09-26T19:10:39.630Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {andrienko:cp:2017},\n source_type = {article},\n private_publication = {false},\n bibtype = {article},\n author = {Andrienko, D A and Boyd, I D},\n journal = {Chemical Physics}\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 \n A Conservative, Entropic Multispecies BGK Model.\n \n \n \n \n\n\n \n\n\n\n Journal of Statistical Physics, 168(4): 826-856. 8 2017.\n \n\n\n\n
\n\n\n\n \n \n $\"A$ 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\n\n

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@article{\n title = {A Conservative, Entropic Multispecies BGK Model},\n type = {article},\n year = {2017},\n keywords = {BGK,Boltzmann equation,H theorem,Kinetic theory,Multispecies flow,Plasma physics,Transport coefficients},\n pages = {826-856},\n volume = {168},\n month = {8},\n publisher = {Springer New York LLC},\n day = {1},\n id = {f8ec961d-63cd-31bd-bd2d-509a9f84508b},\n created = {2022-02-09T23:53:56.016Z},\n accessed = {2022-02-08},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-02-09T23:53:56.710Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {hauck:jsp:2017},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Haack, Jeffrey R. and Hauck, Cory D. and Murillo, Michael S.},\n doi = {10.1007/S10955-017-1824-9/FIGURES/5},\n journal = {Journal of Statistical Physics},\n number = {4}\n}

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\n \n\n \n \n Viladegut, A.; Düzel, Ü.; and Chazot, O.\n\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\n Chemical Physics, 485-486: 88-97. 3 2017.\n \n\n\n\n
\n\n\n\n \n \n $\"Diffusion$ 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

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@article{\n title = {Diffusion effects on the determination of surface catalysis in Inductively Coupled Plasma facility},\n type = {article},\n year = {2017},\n keywords = {Boundary layer,Chemical reactions,Flat plate,Plasmatron,Wall catalysis},\n pages = {88-97},\n volume = {485-486},\n month = {3},\n publisher = {North-Holland},\n day = {1},\n id = {e4cc4bc6-cad9-31aa-bbf8-8112ab1d9b5f},\n created = {2022-06-08T16:25:04.950Z},\n accessed = {2022-06-08},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-06-08T16:25:05.715Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {viladegut:cp:2017},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Viladegut, Alan and Düzel, Ümran and Chazot, Olivier},\n doi = {10.1016/J.CHEMPHYS.2017.02.002},\n journal = {Chemical Physics}\n}

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\n \n\n \n \n Boyd; and Schwartzentruber\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{\n title = {Nonequilibrium Gas Dynamics and Molecular Simulation},\n type = {book},\n year = {2017},\n publisher = {Cambridge University Press},\n id = {ea0ec366-31c5-3f68-9c09-006f2b81e1b6},\n created = {2022-06-09T15:10:38.814Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-06-09T20:17:40.760Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {boyd:2017},\n source_type = {book},\n private_publication = {false},\n bibtype = {book},\n author = {Boyd, undefined and Schwartzentruber, undefined}\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 7TH EUROPEAN CONFERENCE FOR AERONAUTICS AND SPACE SCIENCES (EUCASS), 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{\n title = {IXV Thermal Protection System Post-Flight Preliminary analysis},\n type = {inproceedings},\n year = {2017},\n id = {4a571d5b-e74b-3c7e-b881-c4211260a677},\n created = {2022-06-09T15:58:22.037Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-06-09T15:58:22.037Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {buffenoir:eucass:2017},\n private_publication = {false},\n bibtype = {inproceedings},\n author = {Buffenoir, F. and Pichon, T. and Barreteau, R.},\n doi = {10.13009/EUCASS2017-330},\n booktitle = {7TH EUROPEAN CONFERENCE FOR AERONAUTICS AND SPACE SCIENCES (EUCASS)}\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. 10 2017.\n \n\n\n\n
\n\n\n\n \n \n $\"Survey$ Website\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{\n title = {Survey of blunt-body supersonic dynamic stability},\n type = {article},\n year = {2017},\n keywords = {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 pages = {109-127},\n volume = {54},\n websites = {https://arc.aiaa.org/doi/10.2514/1.A33552},\n month = {10},\n publisher = {American Institute of Aeronautics and Astronautics Inc.},\n day = {17},\n id = {ac3515d5-7907-38e8-a950-34083a34678f},\n created = {2022-06-13T16:56:23.169Z},\n accessed = {2022-06-13},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-06-13T16:57:41.894Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {kazemba:jsr:2017},\n private_publication = {false},\n bibtype = {article},\n author = {Kazemba, Cole D. and Braun, Robert D. and Clark, Ian G. and Schoenenberger, Mark},\n doi = {10.2514/1.A33552},\n journal = {Journal of Spacecraft and Rockets},\n number = {1}\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 AIAA SciTech Forum - 55th AIAA Aerospace Sciences Meeting, 2017. AIAA Paper 2017-1437\n \n\n\n\n
\n\n\n\n \n \n $\"CFD$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\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{\n title = {CFD simulations of the supersonic inflatable aerodynamic decelerator (SIAD) ballistic range tests},\n type = {inproceedings},\n year = {2017},\n websites = {https://arc.aiaa.org/doi/10.2514/6.2017-1437},\n publisher = {AIAA Paper 2017-1437},\n id = {ae42bdf5-5462-3b98-9824-8412a7816b8c},\n created = {2022-06-21T15:40:05.456Z},\n accessed = {2022-06-21},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-06-21T15:40:05.456Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {brock:scitech:2017},\n private_publication = {false},\n abstract = {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 bibtype = {inproceedings},\n author = {Brock, Joseph M. and Stern, Eric C. and Wilder, Michael C.},\n doi = {10.2514/6.2017-1437},\n booktitle = {AIAA SciTech Forum - 55th AIAA Aerospace Sciences Meeting}\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 \n Adaptive coarse graining method for energy transfer and dissociation kinetics of polyatomic species.\n \n \n \n \n\n\n \n\n\n\n The Journal of Chemical Physics, 147(5): 054107. 8 2017.\n \n\n\n\n
\n\n\n\n \n \n $\"Adaptive$ 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{\n title = {Adaptive coarse graining method for energy transfer and dissociation kinetics of polyatomic species},\n type = {article},\n year = {2017},\n keywords = {chemically reactive flow,dissociation,master equation,maximum entropy methods,nitrogen,reduced order systems},\n pages = {054107},\n volume = {147},\n month = {8},\n publisher = {AIP Publishing LLCAIP Publishing},\n day = {7},\n id = {d1c76e42-33cb-342c-b71f-6c426848ae4a},\n created = {2022-09-26T18:47:34.468Z},\n accessed = {2022-09-26},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-09-26T18:47:35.007Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {sahai:jcp:2017},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Sahai, A. and Lopez, B. and Johnston, C. O. and Panesi, M.},\n doi = {10.1063/1.4996654},\n journal = {The Journal of Chemical Physics},\n number = {5}\n}

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\n \n 2016\n \n \n (17)\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 \n Limits for thermionic emission from leading edges of hypersonic vehicles.\n \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 $\"Limits$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\n \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{\n title = {Limits for thermionic emission from leading edges of hypersonic vehicles},\n type = {inproceedings},\n year = {2016},\n pages = {1-15},\n websites = {https://arc.aiaa.org/doi/abs/10.2514/6.2016-0507},\n publisher = {AIAA Paper 2016-0507},\n city = {San Diego, CA},\n id = {344d754e-9e71-32b1-bc62-1cb38eebe0ae},\n created = {2021-01-05T20:43:34.963Z},\n accessed = {2021-01-04},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-01-05T20:43:34.963Z},\n read = {false},\n starred = {true},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {hanquist:scitech:2016},\n source_type = {inproceedings},\n private_publication = {false},\n abstract = {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 bibtype = {inproceedings},\n author = {Hanquist, Kyle M. and Boyd, Iain D.},\n doi = {10.2514/6.2016-0507},\n booktitle = {54th AIAA Aerospace Sciences Meeting},\n keywords = {etc}\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 \n Modeling of electron transpiration cooling for hypersonic vehicles.\n \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 $\"Modeling$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\n \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{\n title = {Modeling of electron transpiration cooling for hypersonic vehicles},\n type = {inproceedings},\n year = {2016},\n pages = {1-12},\n websites = {https://arc.aiaa.org/doi/abs/10.2514/6.2016-4433},\n publisher = {AIAA Paper 2016-4433},\n city = {Washington, D.C.},\n id = {c15710a6-2b44-33b6-a6d9-b6066053baab},\n created = {2021-01-05T20:43:35.256Z},\n accessed = {2021-01-04},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-01-05T20:43:35.256Z},\n read = {false},\n starred = {true},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {hanquist:aviation:2016},\n source_type = {inproceedings},\n private_publication = {false},\n abstract = {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 bibtype = {inproceedings},\n author = {Hanquist, Kyle M. and Hara, Kentaro and Boyd, Iain D.},\n doi = {10.2514/6.2016-4433},\n booktitle = {46th AIAA Thermophysics Conference},\n keywords = {etc}\n}

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\n \n\n \n \n Parish, E., J.; and Duraisamy, K.\n\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\n Journal of Computational Physics, 305: 758-774. 2016.\n \n\n\n\n
\n\n\n\n \n \n $\"A$ 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

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@article{\n title = {A paradigm for data-driven predictive modeling using field inversion and machine learning},\n type = {article},\n year = {2016},\n keywords = {Closure modeling,Data-driven modeling,Machine learning},\n pages = {758-774},\n volume = {305},\n id = {738e9b1a-6920-3ca5-af12-b3cccffa9573},\n created = {2021-02-17T23:34:27.498Z},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-02-17T23:34:29.725Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {parish:jcp:2016},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Parish, Eric J. and Duraisamy, Karthik},\n doi = {10.1016/j.jcp.2015.11.012},\n journal = {Journal of Computational Physics}\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 \n Efficient Treatment of Structural Deformation for Aerothermoelastic Loads Prediction in High-Speed Flows.\n \n \n \n \n\n\n \n\n\n\n In 15th Dynamics Specialists Conference, 2016. \n \n\n\n\n
\n\n\n\n \n \n $\"Efficient$ 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

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@inproceedings{\n title = {Efficient Treatment of Structural Deformation for Aerothermoelastic Loads Prediction in High-Speed Flows},\n type = {inproceedings},\n year = {2016},\n city = {San Diego, CA},\n id = {440560b1-04c6-362f-9b4c-5e21531e3bc9},\n created = {2021-02-17T23:55:36.110Z},\n accessed = {2021-02-17},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-02-17T23:55:39.795Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {brouwer:aiaa:2016},\n private_publication = {false},\n abstract = {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 bibtype = {inproceedings},\n author = {Brouwer, Kirk R and Gogulapati, Abhijit and Mcnamara, Jack J},\n doi = {10.2514/6.2016-1089},\n booktitle = {15th Dynamics Specialists Conference}\n}

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\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 Economon, T., D.; Palacios, F.; Copeland, S., R.; Lukaczyk, T., W.; and Alonso, J., J.\n\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\n AIAA Journal, 54(3): 828-846. 2016.\n \n\n\n\n
\n\n\n\n \n \n $\"SU2:$ 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

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@article{\n title = {SU2: An open-source suite for multiphysics simulation and design},\n type = {article},\n year = {2016},\n pages = {828-846},\n volume = {54},\n publisher = {American Institute of Aeronautics and Astronautics Inc.},\n id = {5beb7875-6fa4-35d3-bdaf-bdc4c7354ba1},\n created = {2021-05-29T00:13:18.914Z},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-05-29T00:14:14.373Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {economon:aj:2016},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Economon, Thomas D. and Palacios, Francisco and Copeland, Sean R. and Lukaczyk, Trent W. and Alonso, Juan J.},\n doi = {10.2514/1.J053813},\n journal = {AIAA Journal},\n number = {3}\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 The National Academies of Sciences-Engineering-Medicine, 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{\n title = {A Threat to America's Global Vigilance, Reach, and Power: High-Speed Maneuvering Weapons},\n type = {techreport},\n year = {2016},\n institution = {The National Academies of Sciences-Engineering-Medicine},\n id = {c0f174bc-b3f3-3f70-bd30-3536a5144a71},\n created = {2021-05-31T18:11:36.625Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-05-31T18:11:36.625Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {afsb:2016},\n source_type = {techreport},\n private_publication = {false},\n bibtype = {techreport},\n author = {Air Force Studies Board, undefined}\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. 2 2016.\n \n\n\n\n
\n\n\n\n \n \n $\"Air$ Paper\n \n \n \n $\"Air$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\n \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{\n title = {Air Collisional-Radiative Modeling with Heavy-Particle Impact Excitation Processes},\n type = {article},\n year = {2016},\n keywords = {Air Flowing,Boltzmann Constant,Earth,Earth Atmosphere,Einstein Coefficients,Electron Temperature,Franck Condon Principle,Radiative Heating,Shock Layers,Shock Tube},\n pages = {226-239},\n volume = {30},\n websites = {https://arc.aiaa.org/doi/abs/10.2514/1.T4549},\n month = {2},\n publisher = {American Institute of Aeronautics and Astronautics},\n day = {26},\n id = {61199ea8-bcbf-3e6e-b0ea-af592dc07f1c},\n created = {2021-07-11T21:14:34.982Z},\n accessed = {2021-07-11},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-07-11T21:14:59.293Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {lemal:jtht:2016},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Lemal, A. and Jacobs, C. M. and Perrin, M.-Y. and Laux, C. O. and Tran, P. and Raynaud, E.},\n doi = {10.2514/1.T4549},\n journal = {Journal of Thermophysics and Heat Transfer},\n number = {1}\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 ECCOMAS Congress 2016 - Proceedings of the 7th European Congress on Computational Methods in Applied Sciences and Engineering, 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 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{\n title = {Assessment of the fluid-structure interaction capabilities for aeronautical applications of the open-source solver SU2},\n type = {inproceedings},\n year = {2016},\n id = {8c041358-70f6-3086-986f-7ad074532075},\n created = {2021-10-26T18:38:49.717Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-10-26T18:38:49.717Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {sanchez:eccomas:2016},\n private_publication = {false},\n bibtype = {inproceedings},\n author = {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 booktitle = {ECCOMAS Congress 2016 - Proceedings of the 7th European Congress on Computational Methods in Applied Sciences and Engineering}\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

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@inproceedings{\n title = {Mesh Adaptation for SU2 with the INRIA AMG Library},\n type = {inproceedings},\n year = {2016},\n id = {21eb8e58-d492-34ac-a8ce-8b387490b97c},\n created = {2021-10-26T18:44:18.203Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-10-26T18:44:18.203Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {alonso:su2:2016},\n private_publication = {false},\n bibtype = {inproceedings},\n author = {Alonso, J. and Economon, T. and Menier, V.},\n booktitle = {1st Annual SU2 Developers Meeting}\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 \n Efficient Aerodynamic Design using the Discrete Adjoint Method in SU2.\n \n \n \n \n\n\n \n\n\n\n In AIAA AVIATION Forum, 2016. AIAA 2016-3518\n \n\n\n\n
\n\n\n\n \n \n $\"Efficient$ 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 \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{\n title = {Efficient Aerodynamic Design using the Discrete Adjoint Method in SU2},\n type = {inproceedings},\n year = {2016},\n publisher = {AIAA 2016-3518},\n id = {757a7d95-daa1-34eb-9c9f-03acb51b58f4},\n created = {2021-11-06T17:36:23.821Z},\n accessed = {2021-11-06},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-11-06T17:37:16.513Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {albring:avi:2016},\n private_publication = {false},\n bibtype = {inproceedings},\n author = {Albring, Tim and Sagebaum, Max and Gauger, Nicolas R},\n doi = {10.2514/6.2016-3518},\n booktitle = {AIAA AVIATION Forum}\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 31st Symposium on Naval Hydrodynamics, 2016. \n \n\n\n\n
\n\n\n\n \n \n $\"Inverse$ Paper\n \n \n \n $\"Inverse$ Website\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{\n title = {Inverse Method for Determination of the In Situ Hydrodynamic Load Distribution in Multi-Phase Flow},\n type = {inproceedings},\n year = {2016},\n websites = {https://www.researchgate.net/publication/308627046},\n id = {afad234b-1dfc-3db9-8c70-d401332d9f8f},\n created = {2021-11-06T17:55:11.629Z},\n accessed = {2021-11-06},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-11-06T17:55:15.279Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {ward:snh:2016},\n private_publication = {false},\n bibtype = {inproceedings},\n author = {Ward, Jacob and Harwood, Casey M and Young, Yin Lu},\n booktitle = {31st Symposium on Naval Hydrodynamics}\n}

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\n \n\n \n \n Sellier, M.\n\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\n Acta Mech, 227: 913-935. 2016.\n \n\n\n\n
\n\n\n\n \n \n $\"Inverse$ 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

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@article{\n title = {Inverse problems in free surface flows: a review},\n type = {article},\n year = {2016},\n pages = {913-935},\n volume = {227},\n id = {e8d7e764-5c65-3d8d-ada3-11bc7141e797},\n created = {2021-11-06T17:55:12.258Z},\n accessed = {2021-11-06},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-11-06T17:55:15.722Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {sellier:am:2016},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Sellier, Mathieu},\n doi = {10.1007/s00707-015-1477-1},\n journal = {Acta Mech}\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. 9 2016.\n \n\n\n\n
\n\n\n\n \n \n $\"Hard-sphere/pseudo-particle$ 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\n\n

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@article{\n title = {Hard-sphere/pseudo-particle modelling (HS-PPM) for efficient and scalable molecular simulation of dilute gaseous flow and transport},\n type = {article},\n year = {2016},\n keywords = {Dilute gas,hard-sphere,high Knudsen number,micro chemical engineering,micro-flow,molecular dynamics simulation,pseudo-particle modelling},\n pages = {1171-1182},\n volume = {42},\n month = {9},\n publisher = {Taylor & Francis},\n day = {21},\n id = {51c3773f-9e87-3db3-ae06-d45d2b0eedf1},\n created = {2022-06-07T16:08:27.273Z},\n accessed = {2022-06-07},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-06-07T16:11:11.313Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {zhang:ms:2016},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Zhang, Chenglong and Shen, Guofei and Li, Chengxiang and Ge, Wei and Li, Jinghai},\n doi = {10.1080/08927022.2016.1154551},\n journal = {Molecular Simulation},\n number = {14}\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). 11 2016.\n \n\n\n\n
\n\n\n\n \n \n $\"Validation$ Paper\n \n \n \n $\"Validation$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\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{\n title = {Validation simulations of the DSMC code SPARTA},\n type = {article},\n year = {2016},\n volume = {1786},\n websites = {https://aip.scitation.org/doi/abs/10.1063/1.4967566},\n month = {11},\n publisher = {AIP Publishing LLCAIP Publishing},\n day = {15},\n id = {d5da9a79-11e5-37b4-8357-4d9a3dd12aaa},\n created = {2022-06-09T15:19:47.323Z},\n accessed = {2022-06-09},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-06-09T15:19:48.736Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {klothakis:aip:2016},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Klothakis, A. G. and Nikolos, I. K. and Koehler, T. P. and Gallis, M. A. and Plimpton, S. J.},\n doi = {10.1063/1.4967566},\n journal = {AIP Conference Proceedings},\n number = {1}\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. 4 2016.\n \n\n\n\n
\n\n\n\n \n \n $\"Molecular$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\n \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{\n title = {Molecular Dynamics Study of Gas–Surface Interactions in a Force-Driven Flow of Argon through a Rectangular Nanochannel},\n type = {article},\n year = {2016},\n keywords = {Gas-surface interactions,Nano-Poiseuille flow,molecular dynamics method},\n pages = {121-136},\n volume = {20},\n websites = {https://www.tandfonline.com/doi/abs/10.1080/15567265.2016.1215364},\n month = {4},\n publisher = {Taylor & Francis},\n day = {2},\n id = {2f4b6f00-c866-31a1-ac52-369ed58e9af7},\n created = {2022-06-09T15:20:47.148Z},\n accessed = {2022-06-09},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-06-09T15:20:47.148Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {kammara:nmte:2016},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Kammara, Kishore K. and Malaikannan, G. and Kumar, Rakesh},\n doi = {10.1080/15567265.2016.1215364},\n journal = {Nanoscale and Microscale Thermophysical Engineering},\n number = {2}\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. 11 2016.\n \n\n\n\n
\n\n\n\n \n \n $\"Modeling$ Paper\n \n \n \n $\"Modeling$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\n \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{\n title = {Modeling of near-continuum laminar boundary layer shocks using DSMC},\n type = {article},\n year = {2016},\n keywords = {DSMC,Hypersonic separated flows,Shock-wave boundary layer interactions},\n pages = {050004},\n volume = {1786},\n websites = {https://aip.scitation.org/doi/abs/10.1063/1.4967554},\n month = {11},\n publisher = {AIP Publishing LLCAIP Publishing},\n day = {15},\n id = {7d0ad86c-0087-3ef9-b547-77ab3d5d7b05},\n created = {2022-06-09T15:30:11.051Z},\n accessed = {2022-06-09},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-06-09T15:30:12.458Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {tumuklu:aip:2016},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Tumuklu, Ozgur and Levin, Deborah A. and Gimelshein, Sergey F. and Austin, Joanna M.},\n doi = {10.1063/1.4967554},\n journal = {AIP Conference Proceedings},\n number = {1}\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 \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\n In 54th AIAA Aerospace Sciences Meeting, 2016. AIAA Paper 2016-0505\n \n\n\n\n
\n\n\n\n \n \n $\"State-to-state$ 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

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@inproceedings{\n title = {State-to-state and reduced-order models for dissociation and energy transfer in aerothermal environments},\n type = {inproceedings},\n year = {2016},\n publisher = {AIAA Paper 2016-0505},\n id = {57bec302-053d-3635-aeae-e06d0de8d708},\n created = {2022-09-19T20:24:20.306Z},\n accessed = {2022-09-19},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-09-26T19:19:11.403Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {munafo:scitech:2016},\n private_publication = {false},\n abstract = {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 bibtype = {inproceedings},\n author = {Munafò, Alessandro and Venturi, Simone and Macdonald, Obyn and Panesi, Marco},\n doi = {10.2514/6.2016-0505},\n booktitle = {54th AIAA Aerospace Sciences Meeting}\n}

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\n \n 2015\n \n \n (15)\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 \n Comparisons of computations with experiments for electron transpiration cooling at high enthalpies.\n \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 $\"Comparisons$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\n \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{\n title = {Comparisons of computations with experiments for electron transpiration cooling at high enthalpies},\n type = {inproceedings},\n year = {2015},\n pages = {1-13},\n websites = {https://arc.aiaa.org/doi/abs/10.2514/6.2015-2351},\n publisher = {AIAA Paper 2015-2351},\n city = {Dallas, TX},\n id = {5f494b66-f90f-3e82-9e84-bfbcfccaab02},\n created = {2021-01-05T20:43:35.507Z},\n accessed = {2021-01-04},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-01-05T20:43:35.507Z},\n read = {false},\n starred = {true},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {hanquist:aviation:2015},\n source_type = {inproceedings},\n private_publication = {false},\n abstract = {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 bibtype = {inproceedings},\n author = {Hanquist, Kyle M. and Boyd, Iain D.},\n doi = {10.2514/6.2015-2351},\n booktitle = {45th AIAA Thermophysics Conference},\n keywords = {etc}\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 \n\n\n\n
\n\n\n\n \n \n $\"Evaluation$ 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 \n \n \n\n\n\n

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@article{\n title = {Evaluation of machine learning algorithms for prediction of regions of high Reynolds averaged Navier Stokes uncertainty},\n type = {article},\n year = {2015},\n keywords = {Navier-Stokes equations,decision trees,extrapolation,feature selection,flow simulation,learning (artificial intelligence),support vector machines,turbulence,viscosity},\n volume = {27},\n publisher = {American Institute of Physics Inc.},\n id = {bd6e3374-374a-3198-ba31-f8cbef762d8b},\n created = {2021-02-17T23:34:27.500Z},\n accessed = {2021-01-12},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-07-23T21:07:17.137Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {ling:pf:2015},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Ling, J. and Templeton, J.},\n doi = {10.1063/1.4927765},\n journal = {Physics of Fluids},\n number = {8}\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. 2 2015.\n \n\n\n\n
\n\n\n\n \n \n $\"Master$ Paper\n \n \n \n $\"Master$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\n \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{\n title = {Master Equation Analysis of Post Normal Shock Waves of Nitrogen},\n type = {article},\n year = {2015},\n keywords = {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 pages = {241-252},\n volume = {29},\n websites = {https://arc.aiaa.org/doi/abs/10.2514/1.T4249},\n month = {2},\n publisher = {American Institute of Aeronautics and Astronautics},\n day = {27},\n id = {4399558b-77fe-3e1c-8381-f29400984e70},\n created = {2021-07-11T21:22:42.768Z},\n accessed = {2021-07-11},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-07-11T21:22:49.245Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {kim:jtht:2015},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Kim, Jae Gang and Boyd, Iain D.},\n doi = {10.2514/1.T4249},\n journal = {Journal of Thermophysics and Heat Transfer},\n number = {2}\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. 5 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{\n title = {Modeling Radio Communication Blackout and Blackout Mitigation in Hypersonic Vehicles},\n type = {article},\n year = {2015},\n pages = {853-862},\n volume = {52},\n month = {5},\n id = {4bb4a756-b12a-32b9-83ba-ba24c649aad9},\n created = {2021-07-19T22:41:41.949Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-07-19T22:41:41.949Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {kundrapu:jsr:2015},\n source_type = {article},\n private_publication = {false},\n bibtype = {article},\n author = {Kundrapu, Madhusudhan and Loverich, John and Beckwith, Kristian and Stoltz, Peter and Shashurin, Alexey and Keidar, Michael},\n journal = {Journal of Spacecraft and Rockets},\n number = {3}\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. 2 2015.\n \n\n\n\n
\n\n\n\n \n \n $\"Strongly$ Paper\n \n \n \n $\"Strongly$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\n \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{\n title = {Strongly Coupled Computation of Material Response and Nonequilibrium Flow for Hypersonic Ablation},\n type = {article},\n year = {2015},\n keywords = {Arbitrary Lagrangian Eulerian,Boundary Layer,Courant Friedrichs Lewy,Freestream Mach Number,Heat Flux,Hypersonic Ablation,Hypersonic Aerothermodynamics,Nonequilibrium Flows,Pyrolysis,Stagnation Point},\n pages = {89-104},\n volume = {52},\n websites = {https://arc.aiaa.org/doi/abs/10.2514/1.A32847},\n month = {2},\n publisher = {American Institute of Aeronautics and Astronautics},\n day = {19},\n id = {117cf66c-731b-3cbc-854b-6f7d72e3e6b8},\n created = {2021-10-03T20:54:08.942Z},\n accessed = {2021-10-03},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-10-03T20:54:10.159Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {martin:jsr:2015},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Martin, Alexandre and Boyd, Iain D.},\n doi = {10.2514/1.A32847},\n journal = {Journal of Spacecraft and Rockets},\n number = {1}\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

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@book{\n title = {Hypersonic Nonequilibrium Flows: Fundamentals and Recent Advances},\n type = {book},\n year = {2015},\n publisher = {AIAA},\n id = {3b313459-7ea6-3c15-b260-cce8a8bc40ac},\n created = {2021-10-25T19:36:52.260Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-10-25T19:36:52.260Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {josyula:2015},\n private_publication = {false},\n bibtype = {book},\n author = {},\n editor = {Josyula, Eswar}\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. 12 2015.\n \n\n\n\n
\n\n\n\n \n \n $\"Surrogate$ Paper\n \n \n \n $\"Surrogate$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\n \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{\n title = {Surrogate modeling of multifidelity data for large samples},\n type = {article},\n year = {2015},\n keywords = {Communications Engineering,Networks},\n pages = {1348-1355},\n volume = {60},\n websites = {https://link.springer.com/article/10.1134/S1064226915120037},\n month = {12},\n publisher = {Springer},\n day = {16},\n id = {7cf49e31-b0c5-3b51-a25d-8d065e86f92d},\n created = {2021-10-25T22:08:31.556Z},\n accessed = {2021-10-25},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-10-25T22:08:32.001Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {burnaev:mmcm:2015},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Burnaev, E. V. and Zaytsev, A. A.},\n doi = {10.1134/S1064226915120037},\n journal = {Journal of Communications Technology and Electronics 2015 60:12},\n number = {12}\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

\n

@article{\n title = {A Pseudo-Compressibility Method for Solving Inverse Problems based on the 3D Incompressible Euler Equations},\n type = {article},\n year = {2015},\n id = {5c80c4ff-7d9b-36b9-9fed-c74174e6475c},\n created = {2021-11-06T17:36:22.099Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-11-06T17:36:22.099Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {ferlauto:ipse:2015},\n private_publication = {false},\n bibtype = {article},\n author = {Ferlauto, M.},\n journal = {Inverse Problems in Science and Engineering}\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

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@article{\n title = {High Fidelity Modeling of Thermal Relaxation and Dissociation of Oxygen},\n type = {article},\n year = {2015},\n pages = {1-25},\n volume = {27},\n id = {580e5bc6-01f9-3518-8b30-963660b6593a},\n created = {2021-12-10T19:48:57.353Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-12-10T19:48:57.353Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {andrienko:pof:2015},\n source_type = {article},\n private_publication = {false},\n bibtype = {article},\n author = {Andrienko, D A and Boyd, I D},\n journal = {Physics of Fluids},\n number = {11601}\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. 2 2015.\n \n\n\n\n
\n\n\n\n \n \n $\"Master$ Paper\n \n \n \n $\"Master$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\n \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{\n title = {Master Equation Analysis of Post Normal Shock Waves of Nitrogen},\n type = {article},\n year = {2015},\n keywords = {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 pages = {241-252},\n volume = {29},\n websites = {https://arc.aiaa.org/doi/abs/10.2514/1.T4249},\n month = {2},\n publisher = {American Institute of Aeronautics and Astronautics},\n day = {27},\n id = {ae4393cf-96ea-38b1-af58-23c9462b7256},\n created = {2021-12-10T19:49:09.780Z},\n accessed = {2021-07-11},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-12-10T19:49:10.488Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {kim:jtht:2015},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Kim, Jae Gang and Boyd, Iain D.},\n doi = {10.2514/1.T4249},\n journal = {Journal of Thermophysics and Heat Transfer},\n number = {2}\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 International Space Planes and Hypersonic Systems and Technologies Conferences, 7 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

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@inproceedings{\n title = {Electron Transpiration Cooling for Hot Aerospace Surfaces},\n type = {inproceedings},\n year = {2015},\n keywords = {etc},\n month = {7},\n publisher = {AIAA Paper 2015-3674},\n city = {Glasgow, Scotland},\n id = {4e8b9b7e-a7bc-326f-af74-5f9bde71f6db},\n created = {2022-04-18T17:36:14.697Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-04-18T17:36:14.697Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {uribarri:hypersonic:2015},\n source_type = {inproceedings},\n private_publication = {false},\n bibtype = {inproceedings},\n author = {Uribarri, Luke A and Allen, Edward H},\n booktitle = {International Space Planes and Hypersonic Systems and Technologies Conferences}\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. 10 2015.\n \n\n\n\n
\n\n\n\n \n \n $\"Object-oriented/data-oriented$ Paper\n \n \n \n $\"Object-oriented/data-oriented$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\n \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{\n title = {Object-oriented/data-oriented design of a direct simulation Monte Carlo algorithm},\n type = {article},\n year = {2015},\n keywords = {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 pages = {1521-1529},\n volume = {52},\n websites = {https://arc.aiaa.org/doi/10.2514/1.A33177},\n month = {10},\n publisher = {American Institute of Aeronautics and Astronautics Inc.},\n day = {6},\n id = {5900fa95-39d7-3603-a9d4-51b89925b60a},\n created = {2022-06-15T18:12:22.860Z},\n accessed = {2022-06-15},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-06-15T18:12:23.535Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {liechty:jsr:2015},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Liechty, Derek S.},\n doi = {10.2514/1.A33177/ASSET/IMAGES/LARGE/FIGURE8.JPEG},\n journal = {Journal of Spacecraft and Rockets},\n number = {6}\n}

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\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

\n\n\n

\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 \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\n In 57th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, 2015. AIAA Paper 2016-0205\n \n\n\n\n
\n\n\n\n \n \n $\"Towards$ Paper\n \n \n \n $\"Towards$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\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{\n title = {Towards a fluid-structure interaction solver for problems with large deformations within the open-source SU2 suite},\n type = {inproceedings},\n year = {2015},\n websites = {https://arc.aiaa.org/doi/10.2514/6.2016-0205},\n publisher = {AIAA Paper 2016-0205},\n id = {efd46aaa-6f36-3598-8fad-11c10b1daeff},\n created = {2022-06-20T12:50:51.052Z},\n accessed = {2022-06-20},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-06-20T12:50:51.808Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {sanchez:scitech:2015},\n private_publication = {false},\n abstract = {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 bibtype = {inproceedings},\n author = {Sanchez, Ruben and Palacios, Rafael and Economon, Thomas D. and Kline, Heather L. and Alonso, Juan J. and Palacios, Francisco},\n doi = {10.2514/6.2016-0205},\n booktitle = {57th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference}\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. 7 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 \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n

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@article{\n title = {Two-dimensional electron gas at the Ti-diffused BiFeO3/SrTiO3 interface},\n type = {article},\n year = {2015},\n keywords = {ab initio calculations,atomic force microscopy,bismuth compounds,chemical interdiffusion,strontium compounds,transmission electron microscopy,two-dimensional electron gas,valence bands},\n pages = {031601},\n volume = {107},\n month = {7},\n publisher = {AIP Publishing LLCAIP Publishing},\n day = {20},\n id = {c528f7f8-c343-341f-a58b-20d3c5c84064},\n created = {2022-07-26T00:31:50.478Z},\n accessed = {2022-07-25},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-07-26T00:31:50.478Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {chen:apl:2015},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {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 doi = {10.1063/1.4926732},\n journal = {Applied Physics Letters},\n number = {3}\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 AIAA Aviation and Aeronautics Forum and Exposition, 6 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{\n title = {Nonequilibrium Modeling of Oxygen in Reflected Shock Tube Flows},\n type = {inproceedings},\n year = {2015},\n month = {6},\n publisher = {AIAA Paper 2014-2961},\n city = {Atlanta, GA},\n id = {3d4b3940-2e20-3302-83cb-3ee3f45dfca4},\n created = {2022-09-14T22:46:38.793Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-09-14T22:46:38.793Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {neitzel:aviation:2014},\n source_type = {inproceedings},\n private_publication = {false},\n bibtype = {inproceedings},\n author = {Neitzel, Kevin J and Kim, Jae Gang and Boyd, Iain D},\n booktitle = {AIAA Aviation and Aeronautics Forum and Exposition}\n}

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\n \n 2014\n \n \n (9)\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 \n Conceptual analysis of electron transpiration cooling for the leading edges of hypersonic vehicles.\n \n \n \n \n\n\n \n\n\n\n In AIAA AVIATION 2014 -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 $\"Conceptual$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\n \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{\n title = {Conceptual analysis of electron transpiration cooling for the leading edges of hypersonic vehicles},\n type = {inproceedings},\n year = {2014},\n websites = {https://arc.aiaa.org/doi/abs/10.2514/6.2014-2674},\n publisher = {AIAA Paper 2014-2674},\n city = {Atlanta, GA},\n id = {f3d029f5-4cd9-35ea-a480-a7a54060b640},\n created = {2021-01-05T20:43:35.203Z},\n accessed = {2021-01-04},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-01-05T20:43:35.203Z},\n read = {false},\n starred = {true},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {alkandry:aviation:2014},\n source_type = {inproceedings},\n private_publication = {false},\n abstract = {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 bibtype = {inproceedings},\n author = {Alkandry, Hicham and Hanquist, Kyle M. and Boyd, Iain D.},\n doi = {10.2514/6.2014-2674},\n booktitle = {AIAA AVIATION 2014 -11th AIAA/ASME Joint Thermophysics and Heat Transfer Conference},\n keywords = {etc}\n}

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\n \n\n \n \n Jewell, J., S.\n\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\n Ph.D. Thesis, 2014.\n \n\n\n\n
\n\n\n\n \n \n $\"Boundary-Layer$ 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

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@phdthesis{\n title = {Boundary-Layer Transition on a Slender Cone in Hypervelocity Flow with Real Gas Effects},\n type = {phdthesis},\n year = {2014},\n institution = {California Institute of Technology},\n department = {Aeronautics},\n id = {ec846117-e183-3553-b6d1-dd8ef38a87a1},\n created = {2021-02-24T00:14:47.390Z},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-02-24T20:26:43.302Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {jewell:thesis:2014},\n private_publication = {false},\n bibtype = {phdthesis},\n author = {Jewell, Joseph S}\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 NASA, 2014.\n \n\n\n\n
\n\n\n\n \n \n $\"Toward$ Paper\n \n \n \n $\"Toward$ Website\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{\n title = {Toward Automatic Verification of Goal-Oriented Flow Simulations},\n type = {techreport},\n year = {2014},\n websites = {https://ntrs.nasa.gov/citations/20150000864},\n institution = {NASA},\n revision = {NASA/TM–2014–218386},\n id = {e55c8438-b566-3fbb-9c74-98ebec842f2d},\n created = {2021-02-25T05:16:54.724Z},\n accessed = {2021-02-24},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-02-25T05:17:01.214Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {cart3d},\n private_publication = {false},\n bibtype = {techreport},\n author = {Nemec, Marian and Aftosmis, Michael J}\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 $\"Modeling$ Paper\n \n \n \n $\"Modeling$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\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{\n title = {Modeling of Heat Transfer Attenuation by Ablative Gases During the Stardust Reentry},\n type = {article},\n year = {2014},\n volume = {29},\n websites = {http://arc.aiaa.org},\n id = {6dc66602-8ba6-3c46-bf15-23a29648bc48},\n created = {2021-09-09T00:22:31.515Z},\n accessed = {2021-09-08},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-09-09T00:22:42.391Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {martin:jtht:2015},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Martin, Alexandre and Boyd, Iain D},\n doi = {10.2514/1.T4202},\n journal = {Journal of Thermophysics and Heat Transfer},\n number = {3}\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 U.S. Army Aviation and Missile Research, Development, and Engineering Center, 2014.\n \n\n\n\n
\n\n\n\n \n \n $\"MISSILE$ Paper\n \n \n \n $\"MISSILE$ Website\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{\n title = {MISSILE DATA COMPENDIUM (DATCOM) User Manual-2014 Revision},\n type = {techreport},\n year = {2014},\n websites = {http://www.dtic.mil},\n city = {AFRL-RQ-WP-TR-2014-0281},\n institution = {U.S. Army Aviation and Missile Research, Development, and Engineering Center},\n id = {16b7069e-198c-33e4-93e5-6f46670a557b},\n created = {2021-10-18T17:59:31.139Z},\n accessed = {2021-10-18},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-10-18T17:59:31.602Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {missile:datcom},\n private_publication = {false},\n bibtype = {techreport},\n author = {Rosema, Christopher and Doyle, Joshua and Blake, William B}\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 Journal of Thermophysics and Heat Transfer, 28(2): 191-202. 2014.\n \n\n\n\n
\n\n\n\n \n \n $\"Porous-material$ 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

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@article{\n title = {Porous-material analysis toolbox based on openfoam and applications},\n type = {article},\n year = {2014},\n pages = {191-202},\n volume = {28},\n id = {0ec1c82f-2565-34eb-9f09-b69b00ffa4a2},\n created = {2021-11-12T22:47:25.942Z},\n file_attached = {true},\n profile_id = {f36664cd-6b95-3668-b717-812e4c7779dc},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-11-12T23:02:57.074Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {Lachaud:jtht:2014},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Lachaud, Jean and Mansour, Nagi N.},\n doi = {10.2514/1.T4262},\n journal = {Journal of Thermophysics and Heat Transfer},\n number = {2}\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 O2-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

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@article{\n title = {Thermochemical nonequilibrium analysis of O2-Ar based on state-resolved kinetics},\n type = {article},\n year = {2014},\n pages = {76-85},\n volume = {446},\n id = {2403437c-3b22-3044-a00a-1d45d3c08173},\n created = {2021-12-10T19:51:02.391Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-09-26T19:15:03.466Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {kim:cp:2015},\n source_type = {article},\n private_publication = {false},\n bibtype = {article},\n author = {Kim, J G and Boyd, I D},\n journal = {Chemical Physics}\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 Sandia National Laboratories, 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

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@techreport{\n title = {Dakota, A Multilevel Parallel Object-Oriented Framework for Design Optimization, Parameter Estimation, Uncertainty Quantification, and Sensitivity Analysis: Version 6.0 User's Manual},\n type = {techreport},\n year = {2014},\n issue = {Sandia Technical Report SAND2014-4633},\n institution = {Sandia National Laboratories},\n id = {4478938b-14f3-3f33-ad5c-dd72eb460e86},\n created = {2022-06-08T14:36:23.281Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-06-08T14:36:23.281Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {dakota:2014},\n source_type = {techreport},\n private_publication = {false},\n bibtype = {techreport},\n author = {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}

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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. 8 2014.\n \n\n\n\n
\n\n\n\n \n \n $\"Assessment$ Paper\n \n \n \n $\"Assessment$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\n \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{\n title = {Assessment of the reconstructed aerodynamics of the mars science laboratory entry vehicle},\n type = {article},\n year = {2014},\n keywords = {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 pages = {1076-1093},\n volume = {51},\n websites = {https://arc.aiaa.org/doi/10.2514/1.A32794},\n month = {8},\n publisher = {American Institute of Aeronautics and Astronautics Inc.},\n day = {26},\n id = {bf6080b7-4b76-3498-8689-680cb694ad68},\n created = {2022-06-21T16:16:56.410Z},\n accessed = {2022-06-21},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-06-21T16:16:57.184Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {schoenenberger:jsr:2014},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Schoenenberger, Mark and Van Norman, John and Karlgaard, Chris and Kutty, Prasad and Way, David},\n doi = {10.2514/1.A32794/ASSET/IMAGES/LARGE/FIGURE23.JPEG},\n journal = {Journal of Spacecraft and Rockets},\n number = {4}\n}

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\n \n 2013\n \n \n (7)\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. 9 2013.\n \n\n\n\n
\n\n\n\n \n \n $\"Multidisciplinary$ Paper\n \n \n \n $\"Multidisciplinary$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\n \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{\n title = {Multidisciplinary design optimization: A survey of architectures},\n type = {article},\n year = {2013},\n keywords = {Aerodynamic Loads,Aircraft Design,Computing,Lagrange Multipliers,MDO,Numerical Optimization,Sequential Linear Programming,Sequential Quadratic Programming,Structural Analysis,Structural Optimization},\n pages = {2049-2075},\n volume = {51},\n websites = {http://arc.aiaa.org},\n month = {9},\n publisher = {American Institute of Aeronautics and Astronautics},\n day = {20},\n id = {fea352bb-7a06-3a2a-8d22-8299a7096ed1},\n created = {2021-05-29T00:09:06.346Z},\n accessed = {2021-05-28},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-05-29T00:09:18.392Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {martins:aj:2013},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Martins, Joaquim R.R.A. and Lambe, Andrew B.},\n doi = {10.2514/1.J051895},\n journal = {AIAA Journal},\n number = {9}\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
\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{\n title = {State-Resolved Master Equation Analysis of Thermochemical Nonequilibrium of Nitrogen},\n type = {article},\n year = {2013},\n pages = {237-246},\n volume = {415},\n id = {0a149fd3-8839-3c5a-8ad7-605ae71a1b49},\n created = {2021-06-25T05:52:15.767Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-06-25T05:52:15.767Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {kim:cp:2013},\n source_type = {article},\n private_publication = {false},\n bibtype = {article},\n author = {Kim, J G and Boyd, I D},\n journal = {Chemical Physics},\n number = {3}\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). 3 2013.\n \n\n\n\n
\n\n\n\n \n \n $\"Elaboration$ Paper\n \n \n \n $\"Elaboration$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\n \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{\n title = {Elaboration of collisional–radiative models for flows related to planetary entries into the Earth and Mars atmospheres},\n type = {article},\n year = {2013},\n volume = {22},\n websites = {https://iopscience.iop.org/article/10.1088/0963-0252/22/2/025008,https://iopscience.iop.org/article/10.1088/0963-0252/22/2/025008/meta},\n month = {3},\n publisher = {IOP Publishing},\n day = {1},\n id = {b23c0504-f5f8-3229-b806-37d27c787035},\n created = {2021-07-11T21:16:18.458Z},\n accessed = {2021-07-11},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-07-11T21:16:25.740Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {bultel:psst:2013},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Bultel, Arnaud and Annaloro, Julien},\n doi = {10.1088/0963-0252/22/2/025008},\n journal = {Plasma Sources Science and Technology},\n number = {2}\n}

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\n \n\n \n \n Robertson, S.\n\n\n \n \n \n \n \n Sheaths in laboratory and space plasmas.\n \n \n \n \n\n\n \n\n\n\n Plasma Physics and Controlled Fusion, 55(9). 7 2013.\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{\n title = {Sheaths in laboratory and space plasmas},\n type = {article},\n year = {2013},\n volume = {55},\n month = {7},\n publisher = {IOP Publishing},\n day = {30},\n id = {c907a74d-56dd-372c-9c09-062691fd3af8},\n created = {2021-07-19T21:17:52.001Z},\n accessed = {2021-07-19},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-07-19T21:18:02.898Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {robertson:ppcf:2013},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Robertson, Scott},\n doi = {10.1088/0741-3335/55/9/093001},\n journal = {Plasma Physics and Controlled Fusion},\n number = {9}\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., 5 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 abstract \n \n\n \n\n \n \n \n \n \n \n \n\n \n \n \n\n\n\n

\n

@book{\n title = {Ablative Thermal Protection Systems Modeling},\n type = {book},\n year = {2013},\n month = {5},\n publisher = {American Institute of Aeronautics and Astronautics, Inc.},\n id = {32b0f709-5715-3558-a199-15a2c309915b},\n created = {2021-07-22T05:49:57.607Z},\n accessed = {2021-07-21},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-07-22T05:49:57.607Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {duffa:2013},\n private_publication = {false},\n abstract = {A B S T R A C T The present longitudinal study described developmental patterns of perceived psychological need sat-isfaction (PNS) from the end of elementary school to the end of high school and their contribution to school adjustment at the end of high school. The first goal thus consisted in estimating whether devel-opmental trajectories of perceived PNS were homogeneous (i.e., all students reported similar developmental patterns) or heterogeneous (i.e., there were several distinct developmental trajectories). The second goal involved comparing trajectory groups on dimensions of school adjustment (social, academic, and emotional– personal). A stratified sample of 609 students (277 boys, 332 girls) was surveyed annually on a 6-year period, from the end of elementary school until the end of high school. Results of group-based trajec-tory modeling (Nagin, 1999, 2005) revealed that developmental trajectories of PNS were heterogeneous for autonomy, competence, and relatedness. For each need, four distinct developmental patterns were identified. These trajectories varied in shape, composition, and magnitude such that some students re-ported increasing PNS over time while others reported stable or decreasing PNS. Results from multivariate analyses revealed that students in upper trajectories (e.g., reporting higher levels of PNS, either stable or increasing) generally reported higher levels of academic, social, and personal–emotional adjustment at the end of high school. Results are discussed with respect to their implications for research and interventions.},\n bibtype = {book},\n author = {Duffa, Georges},\n doi = {10.2514/4.101717}\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
\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{\n title = {Numerical Prediction of Hypersonic Flowfields Including Effects of Electron Translational Nonequilibrium},\n type = {article},\n year = {2013},\n pages = {593-606},\n volume = {27},\n id = {5bd14e49-3d48-3bab-affa-fadc901d2a12},\n created = {2021-08-31T00:24:43.575Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-08-31T00:24:43.575Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {farbar:jtht:2013},\n source_type = {article},\n private_publication = {false},\n bibtype = {article},\n author = {Farbar, Erin and Boyd, Iain D and Martin, Alexandre},\n journal = {Journal of Thermophysics and Heat Transfer},\n number = {4}\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 54th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, 2013. \n \n\n\n\n
\n\n\n\n \n \n $\"A$ Paper\n \n \n \n $\"A$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\n \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{\n title = {A Structures Perspective on the Challenges Associated with Analyzing a Reusable Hypersonic Platform},\n type = {inproceedings},\n year = {2013},\n websites = {http://arc.aiaa.org},\n id = {de817553-d41e-36c4-9bc1-9c63c45c54bc},\n created = {2021-10-28T19:49:15.846Z},\n accessed = {2021-10-28},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-10-28T19:49:16.474Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {eason:aiaa:2013},\n private_publication = {false},\n abstract = {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 bibtype = {inproceedings},\n author = {Eason, Thomas G and Spottswood, S Michael and Chona, Ravi and Penmetsa, Ravi},\n doi = {10.2514/6.2013-1747},\n booktitle = { 54th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference}\n}

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\n \n 2012\n \n \n (16)\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

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@article{\n title = {High performance modeling of atmospheric re-entry vehicles},\n type = {article},\n year = {2012},\n pages = {1-12},\n volume = {341},\n id = {7a701863-5809-3f84-92bb-919643fcfd03},\n created = {2021-02-17T23:19:30.752Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-02-17T23:19:30.752Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {martin:jop:2012},\n source_type = {article},\n private_publication = {false},\n bibtype = {article},\n author = {Martin, Alexandre and Scalabrin, Leonardo C and Boyd, Iain D},\n journal = {Journal of Physics: Conference Series}\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 \n link\n \n \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{\n title = {Physics and Computation of Aero-Optics},\n type = {article},\n year = {2012},\n pages = {299-321},\n volume = {44},\n id = {a6cfb58d-7774-318e-bf0b-5a4456981166},\n created = {2021-05-31T18:11:36.530Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-05-31T18:11:36.530Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {wang:arofm:2012},\n source_type = {article},\n private_publication = {false},\n bibtype = {article},\n author = {Wang, Meng and Mani, Ali and Gordeyev, Stanislav},\n journal = {Annual Review of Fluid Mechanics}\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 N2(1Σ+g)-N(4Su) 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

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@article{\n title = {Rovibrational internal energy transfer and dissociation of N2(1Σ+g)-N(4Su) system in hypersonic flows},\n type = {article},\n year = {2012},\n pages = {1-16},\n volume = {138},\n id = {fe7e02bc-5fca-31e6-af8f-acd823fada91},\n created = {2021-06-25T05:52:15.377Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-07-12T10:41:10.314Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {panesi:jcp:2013},\n source_type = {article},\n private_publication = {false},\n bibtype = {article},\n author = {Panesi, Marco and Jaffe, Richard L and Schwenke, David W and Magin, Thierry E},\n journal = {The Journal of Chemical Physics},\n number = {4}\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 \n Modeling of Electron Energy Phenomena in Hypersonic Flows.\n \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 $\"Modeling$ 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

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@article{\n title = {Modeling of Electron Energy Phenomena in Hypersonic Flows},\n type = {article},\n year = {2012},\n volume = {26},\n id = {46b6170d-9554-3060-9f61-1b1e4c02528c},\n created = {2021-07-11T20:32:26.099Z},\n accessed = {2021-07-11},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-07-11T20:32:38.275Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {kim:jtht:2012},\n private_publication = {false},\n abstract = {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=2u 2  v 2  w 2  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=2u 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  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 bibtype = {article},\n author = {Kim, Minkwan and Gülhan, Ali and Boyd, Iain D},\n doi = {10.2514/1.T3716},\n journal = {Journal of Thermophysics and Heat Transfer},\n number = {2}\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=2u 2 v 2 w 2 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=2u 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 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 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. 5 2012.\n \n\n\n\n
\n\n\n\n \n \n $\"Fire$ Paper\n \n \n \n $\"Fire$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\n \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{\n title = {Fire II Flight Experiment Analysis by Means of a Collisional-Radiative Model},\n type = {article},\n year = {2012},\n keywords = {Degree of Ionization,Energy Distribution,Flow Characteristics,Freestream,One Dimensional Flow,Quasi Steady States,Rankine Hugoniot Relation,Shock Layers,Spontaneous Emission,Thermal Nonequilibrium},\n pages = {236-248},\n volume = {23},\n websites = {https://arc.aiaa.org/doi/abs/10.2514/1.39034},\n month = {5},\n publisher = {American Institute of Aeronautics and Astronautics Inc.},\n day = {23},\n id = {32c8f84e-2b90-3181-bb66-6bc0cb95fa6e},\n created = {2021-07-11T21:08:46.991Z},\n accessed = {2021-07-11},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-07-11T21:09:00.193Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {panesi:jtht:2012},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Panesi, Marco and Magin, Thierry and Bourdon, Anne and Bultel, Arnaud and Chazot, O.},\n doi = {10.2514/1.39034},\n journal = {Journal of Thermophysics and Heat Transfer},\n number = {2}\n}

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\n \n\n \n \n Dulikravich, G., S., B., H., D., P., S., R., H., R., M., J.\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 \n\n\n\n
\n\n\n\n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\n \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{\n title = {Inverse Problems in Aerodynamics, Heat Transfer, Elasticity and Materials Design},\n type = {article},\n year = {2012},\n keywords = {aerodynamic design,inverse problems,material design,thermoelasticity},\n pages = {405-420},\n volume = {13},\n publisher = {The Korean Society for Aeronautical and Space Sciences},\n id = {d3295d67-e3f7-3fb7-930c-f566d4132cd7},\n created = {2021-11-06T17:36:23.153Z},\n accessed = {2021-11-06},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-11-06T17:36:23.153Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {dulikravich:ijass:2012},\n private_publication = {false},\n abstract = {A number of existing and emerging concepts for formulating solution algorithms applicable to multidisciplinary inverse problems involving aerodynamics, heat conduction, elasticity, and material properties of arbitrary three-dimensional objects are briefly surveyed. Certain unique features of these algorithms and their advantages are sketched for use with boundary element and finite element methods. © The Korean Society for Aeronautical & Space Sciences.},\n bibtype = {article},\n author = {Dulikravich, George S.;Dennis, Brian H.;Baker, Daniel P.;Kennon, Stephen R.;Orlande, Helcio R.B.;Colaco, Marcelo J.;},\n doi = {10.5139/IJASS.2012.13.4.405},\n journal = {International Journal of Aeronautical and Space Sciences},\n number = {4}\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. 10 2012.\n \n\n\n\n
\n\n\n\n \n \n $\"A$ Paper\n \n \n \n $\"A$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\n \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{\n title = {A simulated annealing-based inverse computational fluid dynamics model for unknown parameter estimation in fluid flow problem},\n type = {article},\n year = {2012},\n keywords = {inverse problem,lid-driven cavity flow,simulated annealing,width},\n pages = {499-513},\n volume = {26},\n websites = {https://www.tandfonline.com/doi/abs/10.1080/10618562.2011.632375},\n month = {10},\n publisher = { Taylor & Francis },\n id = {81761cc6-6ca0-323e-bcf2-0009fbbb91d0},\n created = {2021-11-06T17:55:12.870Z},\n accessed = {2021-11-06},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-11-06T17:55:16.332Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {das:ijcfd:2012},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Das, Ranjan},\n doi = {10.1080/10618562.2011.632375},\n journal = {International Journal of Computational Fluid Dynamics},\n number = {9-10}\n}

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\n \n\n \n \n Das, R.\n\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\n Inverse Problems in Science and Engineering, 20(4): 445-462. 6 2012.\n \n\n\n\n
\n\n\n\n \n \n $\"Inverse$ 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\n\n

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@article{\n title = {Inverse analysis of Navier–Stokes equations using simplex search method},\n type = {article},\n year = {2012},\n keywords = {Navier–Stokes equation,Reynold's number,inverse problem,length,parameter estimation,simplex search method,width},\n pages = {445-462},\n volume = {20},\n month = {6},\n publisher = {Taylor & Francis},\n id = {d355e791-8cfb-3b6f-a4f9-1978a594b857},\n created = {2021-11-06T17:55:13.487Z},\n accessed = {2021-11-06},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-11-06T17:55:16.770Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {das:ipse:2012},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Das, Ranjan},\n doi = {10.1080/17415977.2011.629046},\n journal = {Inverse Problems in Science and Engineering},\n number = {4}\n}

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\n \n\n \n \n Nicholson, D., W.\n\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\n Inverse Problems in Science and Engineering, 20(5): 735-748. 9 2012.\n \n\n\n\n
\n\n\n\n \n \n $\"On$ 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

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@article{\n title = {On finite element analysis of an inverse problem in elasticity},\n type = {article},\n year = {2012},\n keywords = {finite element modelling,inverse modelling,matrix nonsingularity condition,mesh modification},\n pages = {735-748},\n volume = {20},\n month = {9},\n publisher = {Taylor & Francis},\n id = {40b18955-eabc-3ad5-bdb8-123a70912993},\n created = {2021-11-06T18:17:59.615Z},\n accessed = {2021-11-06},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-11-06T18:18:02.956Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {nicholson:ipse:2012},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Nicholson, David W.},\n doi = {10.1080/17415977.2012.668677},\n journal = {Inverse Problems in Science and Engineering},\n number = {5}\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. 4 2012.\n \n\n\n\n
\n\n\n\n \n \n $\"Review$ Paper\n \n \n \n $\"Review$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\n \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{\n title = {Review of Output-Based Error Estimation and Mesh Adaptation in Computational Fluid Dynamics},\n type = {article},\n year = {2012},\n keywords = {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 pages = {673-694},\n volume = {49},\n websites = {https://arc.aiaa.org/doi/abs/10.2514/1.J050073},\n month = {4},\n day = {30},\n id = {b8e3cf71-c8c4-3347-9aa9-df81164becc0},\n created = {2022-01-18T03:14:07.744Z},\n accessed = {2022-01-17},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-01-18T03:14:08.264Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {fidkowski:aj:2012},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Fidkowski, Krzysztof J. and Darmofal, David L.},\n doi = {10.2514/1.J050073},\n journal = {AIAA Journal},\n number = {4}\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 \n Numerical Study of Plasma-Assisted Aerodynamic Control for Hypersonic Vehicles.\n \n \n \n \n\n\n \n\n\n\n Journal of Spacecraft and Rockets, 46(3): 568-576. 5 2012.\n \n\n\n\n
\n\n\n\n \n \n $\"Numerical$ 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 \n \n \n \n \n\n\n\n

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@article{\n title = {Numerical Study of Plasma-Assisted Aerodynamic Control for Hypersonic Vehicles},\n type = {article},\n year = {2012},\n keywords = {Bow Shock,Flight Control,Freestream Conditions,Hypersonic Flows,Hypersonic Vehicles,Pressure Coefficient,Thermal Nonequilibrium,Thermal Protection System,Vibrational Energy,Wall Temperature},\n pages = {568-576},\n volume = {46},\n month = {5},\n publisher = {American Institute of Aeronautics and Astronautics Inc.},\n day = {23},\n id = {de9d4be7-3f62-3a10-b9fb-633cb9917241},\n created = {2022-06-08T19:32:01.064Z},\n accessed = {2022-06-08},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-06-08T19:32:02.071Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {bisek:jsr:2012},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Bisek, Nicholas J. and Boyd, Iain D. and Poggie, Jonathan},\n doi = {10.2514/1.39032},\n journal = {Journal of Spacecraft and Rockets},\n number = {3}\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. 5 2012.\n \n\n\n\n
\n\n\n\n \n \n $\"Flight$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\n \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{\n title = {Flight Extrapolation of Plasma Wind Tunnel Stagnation Region Flowfield},\n type = {article},\n year = {2012},\n keywords = {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 pages = {493-499},\n volume = {20},\n websites = {https://arc.aiaa.org/doi/10.2514/1.17185},\n month = {5},\n publisher = {American Institute of Aeronautics and Astronautics Inc.},\n day = {23},\n id = {13805c96-2e27-3f48-9c88-c4b576cf2189},\n created = {2022-06-09T15:50:15.770Z},\n accessed = {2022-06-09},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-06-09T15:50:15.770Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {barbante:jtht:2012},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Barbante, P. F. and Chazot, O.},\n doi = {10.2514/1.17185},\n journal = {Journal of Thermophysics and Heat Transfer},\n number = {3}\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 30th AIAA Applied Aerodynamics Conference 2012, pages 2217-2230, 2012. AIAA Paper 2012-3225\n \n\n\n\n
\n\n\n\n \n \n $\"Estimation$ Paper\n \n \n \n $\"Estimation$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\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{\n title = {Estimation of dynamic stability coefficients for aerodynamic decelerators using CFD},\n type = {inproceedings},\n year = {2012},\n pages = {2217-2230},\n websites = {https://arc.aiaa.org/doi/10.2514/6.2012-3225},\n publisher = {AIAA Paper 2012-3225},\n id = {cb664bc5-3444-39a7-b791-05b333fcce14},\n created = {2022-06-16T20:01:20.241Z},\n accessed = {2022-06-16},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-06-16T20:01:21.170Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {stern:aiaa:2012},\n private_publication = {false},\n abstract = {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 bibtype = {inproceedings},\n author = {Stern, Eric C. and Gidzak, Vladimyr M. and Candler, Graham V.},\n doi = {10.2514/6.2012-3225},\n booktitle = {30th AIAA Applied Aerodynamics Conference 2012}\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 \n Modications and Clarications for the Implementation of the Spalart-Allmaras Turbulence Model.\n \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 $\"Modications$ Paper\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

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@inproceedings{\n title = {Modications and Clarications for the Implementation of the Spalart-Allmaras Turbulence Model},\n type = {inproceedings},\n year = {2012},\n keywords = {Computational Fluid Dynamics,Turbulence Modeling},\n pages = {9-13},\n publisher = {Seventh International Conference on Computational Fluid Dynamics},\n id = {ec34325b-a23e-3558-a227-699291598510},\n created = {2022-11-04T17:07:38.138Z},\n accessed = {2022-11-03},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-11-04T17:07:38.611Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {allmaras:iccfd:2012},\n private_publication = {false},\n abstract = {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 bibtype = {inproceedings},\n author = {Allmaras, Steven R and Johnson, Forrester T and Spalart, Philippe R}\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

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@book{\n title = {Microwave Spectroscopy},\n type = {book},\n year = {2012},\n publisher = {Dover Publications, Inc.},\n id = {8c37095b-39ed-3f41-b31a-e3ea6ad412c8},\n created = {2022-11-17T04:22:20.838Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-11-17T04:22:20.838Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {townes:2012},\n source_type = {book},\n private_publication = {false},\n bibtype = {book},\n author = {Townes, C H and Schawlow, A L}\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. 2012.\n \n\n\n\n
\n\n\n\n \n \n $\"High$ Website\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{\n title = {High resolution spectral analysis of oxygen. I. Isotopically invariant Dunham fit for the X3Σg−, a1Δg, b1Σg+ states},\n type = {article},\n year = {2012},\n pages = {24304},\n volume = {137},\n websites = {https://doi.org/10.1063/1.4719170},\n id = {8a38e5de-851e-3c83-b2ab-acf2893809e4},\n created = {2022-11-17T04:24:53.669Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-11-17T04:24:53.669Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {yu:jcp:2012},\n source_type = {article},\n private_publication = {false},\n bibtype = {article},\n author = {Yu, Shanshan and Miller, Charles E and Drouin, Brian J and Müller, Holger S P},\n doi = {10.1063/1.4719170},\n journal = {The Journal of Chemical Physics},\n number = {2}\n}

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\n \n 2011\n \n \n (4)\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 \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\n In 42nd AIAA Thermophysics Conference, 2011. \n \n\n\n\n
\n\n\n\n \n \n $\"Uncertainty$ 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

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@inproceedings{\n title = {Uncertainty Assessments of 2D and Axisymmetric Hypersonic Shock Wave-Turbulent Boundary Layer Interaction Simulations at Compression Corners},\n type = {inproceedings},\n year = {2011},\n id = {159b5ba4-17ff-3c58-82ea-2dc3e81e4bca},\n created = {2021-02-23T23:52:30.943Z},\n accessed = {2021-02-23},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-02-23T23:52:33.391Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {gnoffo:aiaa:2011},\n private_publication = {false},\n abstract = {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 bibtype = {inproceedings},\n author = {Gnoffo, Peter A and Berry, Scott A and Van Norman, John W},\n doi = {10.2514/6.2011-3142},\n booktitle = {42nd AIAA Thermophysics Conference}\n}

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\n \n\n \n \n Glass, D., E.\n\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\n In 17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference 2011, 2011. AIAA Paper 2011-2304\n \n\n\n\n
\n\n\n\n \n \n $\"Physical$ 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

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@inproceedings{\n title = {Physical challenges and limitations confronting the use of UHTCs on hypersonic vehicles},\n type = {inproceedings},\n year = {2011},\n publisher = {AIAA Paper 2011-2304},\n id = {ee549ba5-c2eb-3a2c-874a-5914e95991dc},\n created = {2021-07-22T05:49:57.604Z},\n accessed = {2021-07-21},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-07-22T05:50:06.702Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {glass:aiaa:2011},\n private_publication = {false},\n abstract = {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 bibtype = {inproceedings},\n author = {Glass, David E.},\n doi = {10.2514/6.2011-2304},\n booktitle = {17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference 2011}\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
\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{\n title = {Emissive probes},\n type = {article},\n year = {2011},\n pages = {1-22},\n volume = {20},\n id = {2c42e1e5-6154-3ecf-9b94-4b575ab89bda},\n created = {2021-07-22T23:16:29.780Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-07-22T23:16:29.780Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {sheehan:psst:2011},\n source_type = {article},\n private_publication = {false},\n bibtype = {article},\n author = {Sheehan, J P and Hershkowitz, N},\n journal = {Plasma Sources Science and Technology},\n number = {6}\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 29th AIAA Applied Aerodynamics Conference 2011, 2011. AIAA Paper 2011-3504\n \n\n\n\n
\n\n\n\n \n \n $\"Overview$ Paper\n \n \n \n $\"Overview$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\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{\n title = {Overview of orion crew module and launch abort vehicle dynamic stability},\n type = {inproceedings},\n year = {2011},\n websites = {https://arc.aiaa.org/doi/10.2514/6.2011-3504},\n publisher = {AIAA Paper 2011-3504},\n id = {4cc50b37-7284-350d-bd1e-69123e2d150c},\n created = {2022-06-21T15:41:57.701Z},\n accessed = {2022-06-21},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-06-21T15:41:58.368Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {owens:aiaa:2011},\n private_publication = {false},\n abstract = {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 bibtype = {inproceedings},\n author = {Bruce Owens, D. and Aubuchon, Vanessa V.},\n doi = {10.2514/6.2011-3504},\n booktitle = {29th AIAA Applied Aerodynamics Conference 2011}\n}

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\n \n 2010\n \n \n (9)\n \n \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 United States Air Force, 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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@techreport{\n title = {Technology Horizons: A Vision for Air Force Science and Technology for 2010-30},\n type = {techreport},\n year = {2010},\n institution = {United States Air Force},\n id = {82646aea-0891-3185-a443-47ac442dea54},\n created = {2021-05-31T18:11:36.263Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-05-31T18:11:36.263Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {ocs:2010},\n source_type = {techreport},\n private_publication = {false},\n bibtype = {techreport},\n author = {Office of Chief Scientist, undefined}\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 \n The Potential Role of Electronically-Excited States in Recombining Flows.\n \n \n \n \n\n\n \n\n\n\n In 48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition, 2010. \n \n\n\n\n
\n\n\n\n \n \n $\"The$ 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

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@inproceedings{\n title = {The Potential Role of Electronically-Excited States in Recombining Flows},\n type = {inproceedings},\n year = {2010},\n id = {0dc57e66-7668-33d6-b653-93121440c5f4},\n created = {2021-07-11T21:22:42.774Z},\n accessed = {2021-07-11},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-07-11T21:22:51.323Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {candler:scitech:2010},\n private_publication = {false},\n abstract = {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 bibtype = {inproceedings},\n author = {Candler, Graham V and Doraiswamy, Sriram and Kelley, J Daniel},\n doi = {10.2514/6.2010-912},\n booktitle = {48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition}\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 48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition, 2010. American Institute of Aeronautics and Astronautics Inc.\n \n\n\n\n
\n\n\n\n \n \n $\"High$ Paper\n \n \n \n $\"High$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\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{\n title = {High fidelity aero-optical analysis},\n type = {inproceedings},\n year = {2010},\n websites = {https://arc.aiaa.org/doi/abs/10.2514/6.2010-433},\n publisher = {American Institute of Aeronautics and Astronautics Inc.},\n id = {dcc2c880-74d8-3278-be4e-b01d336e1bc6},\n created = {2021-07-12T04:45:02.941Z},\n accessed = {2021-07-11},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-07-12T04:46:00.780Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {white:scitech:2010},\n private_publication = {false},\n abstract = {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 bibtype = {inproceedings},\n author = {White, Michael D. and Morgan, Philip E. and Visbal, Miguel R.},\n doi = {10.2514/6.2010-433},\n booktitle = {48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition}\n}

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\n \n\n \n \n Lamnaouer, M.\n\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\n Ph.D. Thesis, 2010.\n \n\n\n\n
\n\n\n\n \n \n $\"Numerical$ 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

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@phdthesis{\n title = {Numerical Modeling of the Shock Tube Flow Fields Before and During Ignition Delay Time Experiments at Practical Conditions},\n type = {phdthesis},\n year = {2010},\n institution = {University of Central Florida},\n department = {Department of Mechanical, Materials, and Aerospace Engineering},\n id = {496e4176-09e0-3732-b36d-0e149383d501},\n created = {2021-07-12T04:56:12.179Z},\n accessed = {2021-07-11},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-07-12T04:56:38.468Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {lamnaouer:2010},\n private_publication = {false},\n bibtype = {phdthesis},\n author = {Lamnaouer, Mouna}\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
\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{\n title = {The Importance of the Ninth Grade on High School Graduation Rates and Student Success},\n type = {article},\n year = {2010},\n pages = {60-64},\n volume = {76},\n id = {6b09a483-f8a4-3333-b265-4c7af6abf022},\n created = {2021-07-23T18:35:38.247Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-07-23T18:39:22.848Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {mccallumore:ed:2010},\n private_publication = {false},\n bibtype = {article},\n author = {McCallumore, Kyle M. and Sparapani, Ervin F.},\n journal = {Education Digest: Essential Readings Condensed for Quick Review},\n number = {2}\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 \n\n\n\n
\n\n\n\n \n \n $\"An$ Paper\n \n \n \n $\"An$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\n \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{\n title = {An algorithm for fast optimal Latin hypercube design of experiments},\n type = {article},\n year = {2010},\n keywords = {Latin hypercube sampling,design of computer experiments,experimental design,translational propagation algorithm},\n pages = {135-156},\n volume = {82},\n websites = {https://onlinelibrary.wiley.com/doi/full/10.1002/nme.2750,https://onlinelibrary.wiley.com/doi/abs/10.1002/nme.2750,https://onlinelibrary.wiley.com/doi/10.1002/nme.2750},\n publisher = {John Wiley & Sons, Ltd},\n id = {71d58e18-da71-3a2d-ace2-5902911529e3},\n created = {2021-10-25T22:10:10.064Z},\n accessed = {2021-10-25},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-10-25T22:10:10.491Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {viana:nme:2009},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Viana, Felipe A. C. and Venter, Gerhard and Balabanov, Vladimir},\n doi = {10.1002/NME.2750},\n journal = {International Journal for Numerical Methods in Engineering},\n number = {2}\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 $\"Approximate$ Paper\n \n \n \n $\"Approximate$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\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{\n title = {Approximate Modeling of Unsteady Aerodynamics for Hypersonic Aeroelasticity},\n type = {article},\n year = {2010},\n volume = {47},\n websites = {http://arc.aiaa.org},\n id = {dcd65864-4a75-3ae3-ba92-e2893e3c11cb},\n created = {2021-10-25T22:53:06.660Z},\n accessed = {2021-10-25},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-10-25T22:56:23.805Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {mcnamara:ja:2010},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {McNamara, Jack J and Crowell, Andrew R and Friedmann, Peretz P and Glaz, Bryan and Gogulapati, Abhijit},\n doi = {10.2514/1.C000190},\n journal = {Journal of Aircraft},\n number = {6}\n}

\n

\n\n\n

\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 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 AIAA Atmospheric Flight Mechanics Conference, 2010. AIAA 2010-7933\n \n\n\n\n
\n\n\n\n \n \n $\"Structural$ Paper\n \n \n \n $\"Structural$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\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{\n title = {Structural Measurements for Enhanced MAV Flight},\n type = {inproceedings},\n year = {2010},\n websites = {http://arc.aiaa.org},\n publisher = {AIAA 2010-7933},\n id = {ed127c20-2502-3863-907f-4677bf14d968},\n created = {2021-11-06T18:17:58.384Z},\n accessed = {2021-11-06},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-11-06T18:18:02.504Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {dickinson:aiaa:2010},\n private_publication = {false},\n abstract = {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 bibtype = {inproceedings},\n author = {Dickinson, Ben and Singler, John R and Abate, Gregg},\n doi = {10.2514/6.2010-7933},\n booktitle = {AIAA Atmospheric Flight Mechanics Conference}\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). 1 2010.\n \n\n\n\n
\n\n\n\n \n \n $\"Simulation$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\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{\n title = {Simulation of hard-disk flow in microchannels},\n type = {article},\n year = {2010},\n volume = {81},\n websites = {https://journals.aps.org/pre/abstract/10.1103/PhysRevE.81.011201},\n month = {1},\n publisher = {American Physical Society},\n day = {5},\n id = {3da2415d-2653-3b44-bb2f-9c1d4d2182b3},\n created = {2022-06-09T14:42:09.903Z},\n accessed = {2022-06-09},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-06-09T14:42:09.903Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {shen:pe:2010},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Shen, Guofei and Ge, Wei},\n doi = {10.1103/PHYSREVE.81.011201/FIGURES/24/MEDIUM},\n journal = {Physical Review E - Statistical, Nonlinear, and Soft Matter Physics},\n number = {1}\n}

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\n \n 2009\n \n \n (6)\n \n \n

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\n \n\n \n \n Perepezko, J., H.\n\n\n \n \n \n \n \n The hotter the engine, the better.\n \n \n \n \n\n\n \n\n\n\n Science, 326(5956): 1068-1069. 11 2009.\n \n\n\n\n
\n\n\n\n \n \n $\"The$ 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

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@article{\n title = {The hotter the engine, the better},\n type = {article},\n year = {2009},\n pages = {1068-1069},\n volume = {326},\n month = {11},\n publisher = {American Association for the Advancement of Science},\n day = {20},\n id = {8eacc43b-e5ee-3315-9c96-52836a0c7a44},\n created = {2021-04-09T21:07:11.331Z},\n accessed = {2021-04-09},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-07-23T20:58:41.300Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {perepezko:s:2009},\n private_publication = {false},\n abstract = {Alloys based on molybdenum or niobium may allow the high-temperature components of jet engines to run hotter and more efficiently.},\n bibtype = {article},\n author = {Perepezko, John H.},\n doi = {10.1126/science.1179327},\n journal = {Science},\n number = {5956}\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 $\"Recommendations$ 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\n \n \n \n \n \n \n \n\n \n \n \n\n\n\n

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@inproceedings{\n title = {Recommendations from the workshop on communications through plasma during hypersonic flight},\n type = {inproceedings},\n year = {2009},\n publisher = {American Institute of Aeronautics and Astronautics Inc.},\n id = {8613aea5-e7c4-3b71-807b-3167108355ce},\n created = {2021-05-31T19:29:52.605Z},\n accessed = {2021-05-31},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-07-12T10:41:10.761Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {jones:af:2009},\n private_publication = {false},\n bibtype = {inproceedings},\n author = {Jones, Charles H.},\n doi = {10.2514/6.2009-1718},\n booktitle = {U.S. Air Force T and E Days 2009}\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 $\"Aero-Optic$ Paper\n \n \n \n $\"Aero-Optic$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\n \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{\n title = {Aero-Optic Distortion in Transonic and Hypersonic Turbulent Boundary Layers},\n type = {article},\n year = {2009},\n volume = {47},\n websites = {http://arc.aiaa.org},\n id = {ad667564-8c74-30c1-a2e9-2bc355d28759},\n created = {2021-07-11T21:50:24.256Z},\n accessed = {2021-07-11},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-07-11T21:51:09.302Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {wyckham:aj:2009},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Wyckham, Christopher M and Smits, Alexander J},\n doi = {10.2514/1.41453},\n journal = {AIAA Journal},\n number = {9}\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 47th AIAA Aerospace Sciences Meeting, 2009. AIAA 2009-670\n \n\n\n\n
\n\n\n\n \n \n $\"Implicit$ Paper\n \n \n \n $\"Implicit$ Website\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{\n title = {Implicit implementation of material response and moving meshes for hypersonic re-entry ablation},\n type = {inproceedings},\n year = {2009},\n websites = {http://arc.aiaa.org},\n publisher = {AIAA 2009-670},\n id = {aee32b46-6ebf-3041-bf39-edfc0e889360},\n created = {2021-10-03T20:54:07.988Z},\n accessed = {2021-10-03},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-10-03T20:54:09.457Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {martin:scitech:2009},\n private_publication = {false},\n bibtype = {inproceedings},\n author = {Martin, Alexandre and Boyd, Iain D},\n doi = {10.2514/6.2009-670},\n booktitle = {47th AIAA Aerospace Sciences Meeting}\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 \n Supersonic Flutter Analysis Based on a Local Piston Theory.\n \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 $\"Supersonic$ 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{\n title = {Supersonic Flutter Analysis Based on a Local Piston Theory},\n type = {article},\n year = {2009},\n volume = {47},\n id = {2e072120-985c-36a3-ade2-67a331b87564},\n created = {2021-10-26T17:56:02.347Z},\n accessed = {2021-10-26},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-10-26T17:56:03.043Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {zhang:aj:2009},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Zhang, Wei-Wei and Ye, Zheng-Yin and Zhang, Chen-An and Liu, Feng},\n doi = {10.2514/1.37750},\n journal = {AIAA Journal},\n number = {10}\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 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 41st AIAA Thermophysics Conference, 2009. American Institute of Aeronautics and Astronautics Inc.\n \n\n\n\n
\n\n\n\n \n \n $\"A$ Paper\n \n \n \n $\"A$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\n \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{\n title = {A mechanism-based finite-rate surface catalysis model for simulating reacting flows},\n type = {inproceedings},\n year = {2009},\n websites = {https://arc.aiaa.org/doi/10.2514/6.2009-3935},\n publisher = {American Institute of Aeronautics and Astronautics Inc.},\n id = {9281e6c1-a331-3f88-893c-01e03b6ea1db},\n created = {2022-06-09T14:34:25.532Z},\n accessed = {2022-06-09},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-06-09T14:34:26.295Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {valentini:tp:2009},\n private_publication = {false},\n abstract = {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 bibtype = {inproceedings},\n author = {Valentini, Paolo and Schwartzentruber, Thomas E. and Cozmuta, Ioana},\n doi = {10.2514/6.2009-3935},\n booktitle = {41st AIAA Thermophysics Conference}\n}

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\n \n 2008\n \n \n (4)\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 \n Adjoint-based adaptive mesh refinement for complex geometries.\n \n \n \n \n\n\n \n\n\n\n In 46th AIAA Aerospace Sciences Meeting and Exhibit, 2008. \n \n\n\n\n
\n\n\n\n \n \n $\"Adjoint-based$ 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

@inproceedings{\n title = {Adjoint-based adaptive mesh refinement for complex geometries},\n type = {inproceedings},\n year = {2008},\n city = {Reno, NV},\n id = {e4487e87-884d-36aa-9444-f15fb622f8cc},\n created = {2021-02-17T23:17:26.005Z},\n accessed = {2021-02-17},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-02-17T23:19:31.034Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {nemec:aiaa:2008},\n private_publication = {false},\n abstract = {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 bibtype = {inproceedings},\n author = {Nemec, Marian and Aftosmis, Michael J. and Wintzer, Mathias},\n doi = {10.2514/6.2008-725},\n booktitle = {46th AIAA Aerospace Sciences Meeting and Exhibit}\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 15th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 2008. American Institute of Aeronautics and Astronautics Inc.\n \n\n\n\n
\n\n\n\n \n \n $\"Ceramic$ Paper\n \n \n \n $\"Ceramic$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\n \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{\n title = {Ceramic matrix composite (CMC) thermal protection systems (TPS) and hot structures for hypersonic vehicles},\n type = {inproceedings},\n year = {2008},\n websites = {http://arc.aiaa.org},\n publisher = {American Institute of Aeronautics and Astronautics Inc.},\n id = {8bc89648-9323-3a1c-9171-44ac8444a5c9},\n created = {2021-05-28T23:42:04.831Z},\n accessed = {2021-05-28},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-05-28T23:43:24.464Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {glass:aiaa:2008},\n private_publication = {false},\n abstract = {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 bibtype = {inproceedings},\n author = {Glass, David E.},\n doi = {10.2514/6.2008-2682},\n booktitle = {15th AIAA International Space Planes and Hypersonic Systems and Technologies Conference}\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{\n title = {Analysis of an Electromagnetic Mitigation Scheme for Reentry Telemetry Through Plasma},\n type = {article},\n year = {2008},\n pages = {1223-1229},\n volume = {45},\n id = {e2afdb82-1185-3518-8faf-009aae1e9476},\n created = {2021-07-19T22:41:41.941Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-07-19T22:41:41.941Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {kim:jsr:2008},\n source_type = {article},\n private_publication = {false},\n bibtype = {article},\n author = {Kim, Minkwan and Keidar, Michael and Boyd, Iain D},\n journal = {Journal of Spacecraft and Rockets},\n number = {6}\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 40th Thermophysics Conference, 2008. AIAA 2008-3805\n \n\n\n\n
\n\n\n\n \n \n $\"Simulation$ Paper\n \n \n \n $\"Simulation$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\n \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{\n title = {Simulation of pyrolysis gas within a thermal protection system},\n type = {inproceedings},\n year = {2008},\n websites = {https://arc.aiaa.org/doi/abs/10.2514/6.2008-3805},\n publisher = {AIAA 2008-3805},\n id = {105726ef-9201-39aa-a94d-87a5d43cff4f},\n created = {2021-10-03T20:54:08.469Z},\n accessed = {2021-10-03},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-10-03T20:54:09.736Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {martin:thermo:2008},\n private_publication = {false},\n abstract = {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 bibtype = {inproceedings},\n author = {Martin, Alexandre and Boyd, Iain D.},\n doi = {10.2514/6.2008-3805},\n booktitle = {40th Thermophysics Conference}\n}

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\n \n 2007\n \n \n (6)\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 Ph.D. Thesis, 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

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@phdthesis{\n title = {Numerical Simulation of Weakly Ionized Hypersonic Flow over Reentry Capsules},\n type = {phdthesis},\n year = {2007},\n city = {Ann Arbor},\n institution = {University of Michigan},\n id = {e8bee7ee-1d23-318d-8b0b-c29458e03f0f},\n created = {2021-02-17T23:19:30.710Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-02-17T23:19:30.710Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {scalabrin:thesis:2007},\n source_type = {phdthesis},\n private_publication = {false},\n bibtype = {phdthesis},\n author = {Scalabrin, Leonardo C}\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 International Forum on Aeroelasticity and Structural Dynamics, 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

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@inproceedings{\n title = {Approximate Modeling of Unsteady Aerodynamic Loads in Hypersonic Aeroelasticity},\n type = {inproceedings},\n year = {2007},\n city = {Stockholm},\n id = {f15a0e96-2674-3db0-afa0-98283d98d0fb},\n created = {2021-10-26T17:53:53.829Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-10-26T17:53:53.829Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {mcnamara:asd:2007},\n private_publication = {false},\n bibtype = {inproceedings},\n author = {McNamara, J. J. and Gogulapati, A. and Friedmann, P. P. and Banavara, N. K.},\n booktitle = {International Forum on Aeroelasticity and Structural Dynamics}\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. 9 2007.\n \n\n\n\n
\n\n\n\n \n \n $\"Aircraft$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\n \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{\n title = {Aircraft parameter estimation using output-error methods},\n type = {article},\n year = {2007},\n keywords = {Aircraft parameter estimation,Modeling and simulation,Output-error},\n pages = {651-664},\n volume = {14},\n websites = {https://www.tandfonline.com/doi/abs/10.1080/17415970600573544},\n month = {9},\n publisher = { Taylor & Francis Group },\n day = {1},\n id = {196bc2bc-fe5e-3346-9f49-064db6b1974a},\n created = {2021-11-06T18:18:00.769Z},\n accessed = {2021-11-06},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-11-06T18:18:00.769Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {goes:ipse:2006},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {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 doi = {10.1080/17415970600573544},\n journal = {Inverse Problems in Science and Engineering},\n number = {6}\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 39th AIAA Thermophysics Conference, 6 2007. American Institute of Aeronautics and Astronautics\n \n\n\n\n
\n\n\n\n \n \n $\"A$ Paper\n \n \n \n $\"A$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\n \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{\n title = {A Multiscale Approach for Building a Mechanism Based Catalysis Model for High Enthalpy Carbon Dioxide Flow},\n type = {inproceedings},\n year = {2007},\n websites = {https://arc.aiaa.org/doi/10.2514/6.2007-4399},\n month = {6},\n publisher = {American Institute of Aeronautics and Astronautics},\n day = {25},\n city = {Reston, Virigina},\n id = {03f30438-3abc-3a8f-86bb-2b009314445e},\n created = {2022-06-09T14:34:27.212Z},\n accessed = {2022-06-09},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-06-09T14:34:28.041Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {thoemel:tp:2007},\n private_publication = {false},\n abstract = {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 bibtype = {inproceedings},\n author = {Thoemel, Jan and Lukkien, Johan and Chazot, Olivier},\n doi = {10.2514/6.2007-4399},\n booktitle = {39th AIAA Thermophysics Conference}\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 45th AIAA Aerospace Sciences Meeting, volume 2, pages 815-832, 2007. AIAA Paper 2007-0074\n \n\n\n\n
\n\n\n\n \n \n $\"Dynamic$ Paper\n \n \n \n $\"Dynamic$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\n \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{\n title = {Dynamic analysis of atmospheric-entry probes and capsules},\n type = {inproceedings},\n year = {2007},\n pages = {815-832},\n volume = {2},\n websites = {https://arc.aiaa.org/doi/10.2514/6.2007-74},\n publisher = {AIAA Paper 2007-0074},\n id = {fd0480bf-4380-34c6-bf9d-cb98868af178},\n created = {2022-06-15T16:50:47.161Z},\n accessed = {2022-06-15},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-06-15T16:50:47.867Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {murman:aiaa:2007},\n private_publication = {false},\n abstract = {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 bibtype = {inproceedings},\n author = {Murman, Scott M. and Aftosmis, Michael J.},\n doi = {10.2514/6.2007-74},\n booktitle = {45th AIAA Aerospace Sciences Meeting}\n}

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\n \n\n \n \n Gnoffo, P., A.\n\n\n \n \n \n \n \n A Perspective on Computational Aerothermodynamics at NASA.\n \n \n \n \n\n\n \n\n\n\n In 16th Australasian Fluid Mechanics Conference, 2007. \n \n\n\n\n
\n\n\n\n \n \n $\"A$ Paper\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{\n title = {A Perspective on Computational Aerothermodynamics at NASA},\n type = {inproceedings},\n year = {2007},\n id = {e9006c4d-721f-3177-99ae-f518b314463b},\n created = {2022-06-15T17:57:24.523Z},\n accessed = {2022-06-15},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-06-15T17:57:25.190Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {gnoffo:afmc:2007},\n private_publication = {false},\n abstract = {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 bibtype = {inproceedings},\n author = {Gnoffo, Peter A},\n booktitle = {16th Australasian Fluid Mechanics Conference}\n}

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\n \n 2006\n \n \n (9)\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. 1 2006.\n \n\n\n\n
\n\n\n\n \n \n $\"Critical$ Paper\n \n \n \n $\"Critical$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\n \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{\n title = {Critical Hypersonic Aerothermodynamic Phenomena},\n type = {article},\n year = {2006},\n keywords = {Boundary-layer transition,CFD,Flight testing,Ground testing,Hypersonic},\n pages = {129-157},\n volume = {38},\n websites = {http://www.annualreviews.org/doi/10.1146/annurev.fluid.38.050304.092041},\n month = {1},\n publisher = {Annual Reviews},\n day = {16},\n id = {6b92a229-19d8-3494-a065-3e23d8cad3f9},\n created = {2021-02-15T18:21:30.646Z},\n accessed = {2021-02-15},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-02-15T18:21:32.994Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {bertin:arfm:2006},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Bertin, John J. and Cummings, Russell M.},\n doi = {10.1146/annurev.fluid.38.050304.092041},\n journal = {Annual Review of Fluid Mechanics},\n number = {1}\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

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@book{\n title = {Hypersonic and High-Temperature Gas Dynamics},\n type = {book},\n year = {2006},\n publisher = {AIAA},\n edition = {2nd},\n id = {553701c8-274a-3c4a-8507-18c99cd887ec},\n created = {2021-02-24T00:02:09.682Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-02-24T00:02:09.682Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {anderson:2006},\n private_publication = {false},\n bibtype = {book},\n author = {Anderson, John D}\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, 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{\n title = {Space Debris},\n type = {book},\n year = {2006},\n publisher = {Springer-Verlag},\n city = {Berlin},\n id = {9988bf5a-9b2d-303e-8bf2-2a15b3080250},\n created = {2021-03-05T23:37:13.635Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-03-05T23:37:13.635Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {klinkrad:2006},\n private_publication = {false},\n bibtype = {book},\n author = {Klinkrad, Heiner}\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 \n X-43A Hypersonic vehicle technology development.\n \n \n \n \n\n\n \n\n\n\n Acta Astronautica, 59(1-5): 181-191. 7 2006.\n \n\n\n\n
\n\n\n\n \n \n $\"X-43A$ 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

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@article{\n title = {X-43A Hypersonic vehicle technology development},\n type = {article},\n year = {2006},\n pages = {181-191},\n volume = {59},\n month = {7},\n publisher = {Pergamon},\n day = {1},\n id = {bb043103-1ed6-354d-bc35-ba20275fa7ff},\n created = {2021-05-28T23:42:04.574Z},\n accessed = {2021-05-28},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-05-28T23:44:11.051Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {voland:aa:2006},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Voland, Randall T. and Huebner, Lawrence D. and McClinton, Charles R.},\n doi = {10.1016/j.actaastro.2006.02.021},\n journal = {Acta Astronautica},\n number = {1-5}\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 Proceedings 30th Conference of the International Group for the Psychology of Mathematics Education, 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{\n title = {The transition from arithmetic to algebra: to reason, explain, argue, generalize and justify},\n type = {inproceedings},\n year = {2006},\n pages = {225-232},\n id = {be302c1c-7b91-3ff2-af3f-53dcefbaf0db},\n created = {2021-07-23T18:50:12.089Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-07-23T18:50:12.089Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {breiteig:igpme:2006},\n private_publication = {false},\n bibtype = {inproceedings},\n author = {Breiteig, T. and Grevholm, B.},\n booktitle = {Proceedings 30th Conference of the International Group for the Psychology of Mathematics Education}\n}

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\n \n\n \n \n Sadiki, A.; and Janicka, J.\n\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\n International Journal of Thermal Sciences, 45(8): 760-773. 8 2006.\n \n\n\n\n
\n\n\n\n \n \n $\"Unsteady$ 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

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@article{\n title = {Unsteady methods (URANS and LES) for simulation of combustion systems},\n type = {article},\n year = {2006},\n pages = {760-773},\n volume = {45},\n month = {8},\n publisher = {Elsevier Masson},\n day = {1},\n id = {e5d9d89d-b5a7-3698-ad80-95b2b78820ff},\n created = {2021-10-26T18:13:16.191Z},\n accessed = {2021-10-26},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-10-26T18:13:16.917Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {sadiki:ijts:2006},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Sadiki, A. and Janicka, J.},\n doi = {10.1016/J.IJTHERMALSCI.2005.11.001},\n journal = {International Journal of Thermal Sciences},\n number = {8}\n}

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\n \n\n \n \n Ferlauto, M.; and Marsilio, R.\n\n\n \n \n \n \n \n A viscous inverse method for aerodynamic design.\n \n \n \n \n\n\n \n\n\n\n Computers & Fluids, 35(3): 304-325. 3 2006.\n \n\n\n\n
\n\n\n\n \n \n $\"A$ 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{\n title = {A viscous inverse method for aerodynamic design},\n type = {article},\n year = {2006},\n pages = {304-325},\n volume = {35},\n month = {3},\n publisher = {Pergamon},\n day = {1},\n id = {bc8650df-8109-3ae5-a3e6-07a11b35d6b9},\n created = {2021-11-06T17:36:22.724Z},\n accessed = {2021-11-06},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-11-06T17:36:24.953Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {ferlauto:cf:2006},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Ferlauto, Michele and Marsilio, Roberto},\n doi = {10.1016/J.COMPFLUID.2005.01.003},\n journal = {Computers & Fluids},\n number = {3}\n}

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\n \n\n \n \n Font, G., I.\n\n\n \n \n \n \n \n Boundary-Layer Control with Atmospheric Plasma Discharges.\n \n \n \n \n\n\n \n\n\n\n AIAA Journal, 44(7). 2006.\n \n\n\n\n
\n\n\n\n \n \n $\"Boundary-Layer$ 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

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@article{\n title = {Boundary-Layer Control with Atmospheric Plasma Discharges},\n type = {article},\n year = {2006},\n volume = {44},\n id = {72581d73-61e8-3f24-9970-fa40e0a8b33d},\n created = {2021-11-12T22:50:34.038Z},\n accessed = {2021-11-12},\n file_attached = {true},\n profile_id = {21d83d7d-c530-30ac-9c1c-03ebe266d019},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-11-12T22:59:32.745Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {Font:AJ:2006},\n private_publication = {false},\n abstract = {Recent studies have investigated the use of plasma actuators for the active control of the boundary layer on turbine blades. Although the overall effects have been quantified through experiments, the exact nature of the plasma and its momentum-transfer mechanisms have not been well characterized. In this study, particle-in-cell and Monte Carlo methods are used to computationally explore the plasma discharge and its interaction with the flow. The plasma composition, its methods of momentum addition, and the physics of its generation are quantified. Comparisons with experiments are made in order to support the findings. Simulations indicate that the plasma is generated through an electron avalanche in a dielectric barrier discharge. The plasma is created as the electrons stream to the dielectric on the first half of the electrode bias cycle and stream back on the second half. Momentum is imparted to the flow on both half-cycles, but the ionization is not equal during both half-cycles. This results in the plasma actuator producing a net force in one direction.},\n bibtype = {article},\n author = {Font, Gabriel I},\n doi = {10.2514/1.18542},\n journal = {AIAA Journal},\n number = {7}\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, 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

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@book{\n title = {Viscous Fluid Flow},\n type = {book},\n year = {2006},\n publisher = {McGraw-Hill},\n city = {New York},\n edition = {Third},\n id = {344e2ca3-1f58-38b5-a0e4-40e51a1f089c},\n created = {2022-05-04T20:56:55.320Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-05-04T20:56:55.320Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {white:2006},\n source_type = {book},\n private_publication = {false},\n bibtype = {book},\n author = {White, Frank M}\n}

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\n \n 2005\n \n \n (2)\n \n \n

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\n \n\n \n \n Lips, T.; and Fritsche, B.\n\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\n In Acta Astronautica, volume 57, pages 312-323, 7 2005. Pergamon\n \n\n\n\n
\n\n\n\n \n \n $\"A$ 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

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@inproceedings{\n title = {A comparison of commonly used re-entry analysis tools},\n type = {inproceedings},\n year = {2005},\n keywords = {Re-entry,Risk analysis,Space debris},\n pages = {312-323},\n volume = {57},\n issue = {2-8},\n month = {7},\n publisher = {Pergamon},\n day = {1},\n id = {05165c45-413b-3943-9ae8-b408eff62d91},\n created = {2021-03-06T19:00:16.240Z},\n accessed = {2021-03-06},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-03-06T19:00:20.395Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {lips:aa:2005},\n private_publication = {false},\n abstract = {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 bibtype = {inproceedings},\n author = {Lips, Tobias and Fritsche, Bent},\n doi = {10.1016/j.actaastro.2005.03.010},\n booktitle = {Acta Astronautica}\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 \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\n Plasma Sources Science and Technology, 14(4): 722. 2005.\n \n\n\n\n
\n\n\n\n \n \n $\"Solving$ 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

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@article{\n title = {Solving the Boltzmann equation to obtain electron transport coefficients and rate coefficients for fluid models},\n type = {article},\n year = {2005},\n pages = {722},\n volume = {14},\n publisher = {IOP Publishing},\n id = {1be66e57-f866-34a8-ad92-1ee31021fb93},\n created = {2022-04-18T23:13:59.824Z},\n accessed = {2022-04-18},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-04-18T23:14:00.343Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {hagelaar:psst:2005},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {M Hagelaar, G J and Pitchford, L C},\n doi = {10.1088/0963-0252/14/4/011},\n journal = {Plasma Sources Science and Technology},\n number = {4}\n}

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\n \n 2004\n \n \n (6)\n \n \n

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\n \n\n \n \n Marrone, P., V.; and Treanor, C., E.\n\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\n The Physics of Fluids, 6(9). 2004.\n \n\n\n\n
\n\n\n\n \n \n $\"Chemical$ 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

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@article{\n title = {Chemical Relaxation with Preferential Dissociation from Excited Vibrational Levels},\n type = {article},\n year = {2004},\n volume = {6},\n publisher = {American Institute of PhysicsAIP},\n id = {4b4a0a77-e2fb-32e3-b26c-39044044c8ca},\n created = {2021-08-10T20:34:11.324Z},\n accessed = {2021-08-10},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-08-10T20:34:14.492Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {marrone:pf:1963},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Marrone, Paul V. and Treanor, Charles E.},\n doi = {10.1063/1.1706888},\n journal = {The Physics of Fluids},\n number = {9}\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 34th AIAA Fluid Dynamics Conference, 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

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@inproceedings{\n title = {DNS of Hypersonic Turbulent Boundary Layers},\n type = {inproceedings},\n year = {2004},\n publisher = {AIAA Paper 2004-2337},\n id = {e599d1ac-bb49-30ec-85c0-a471638df37b},\n created = {2021-11-12T22:38:32.129Z},\n accessed = {2021-11-12},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-11-12T22:39:55.637Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {martin:fdc:2004},\n private_publication = {false},\n abstract = {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 bibtype = {inproceedings},\n author = {Martin, M. Pino},\n doi = {10.2514/6.2004-2337},\n booktitle = {34th AIAA Fluid Dynamics Conference}\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 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. Bousquet, O.; von Luxburg, U.; and Rätsch, G., editor(s). Springer Berlin Heidelberg, 2004.\n \n\n\n\n
\n\n\n\n \n \n $\"Advanced$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\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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@inbook{\n type = {inbook},\n year = {2004},\n pages = {63-71},\n websites = {https://doi.org/10.1007/978-3-540-28650-9_4},\n publisher = {Springer Berlin Heidelberg},\n city = {Berlin, Heidelberg},\n id = {ac56edae-a016-3b28-a6ee-1f015a56e00a},\n created = {2022-06-01T20:11:10.044Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-06-01T20:11:10.044Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {Rasmussen2004},\n source_type = {inbook},\n private_publication = {false},\n abstract = {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 bibtype = {inbook},\n author = {Rasmussen, Carl Edward},\n editor = {Bousquet, Olivier and von Luxburg, Ulrike and Rätsch, Gunnar},\n doi = {10.1007/978-3-540-28650-9_4},\n chapter = {Gaussian Processes in Machine Learning},\n title = {Advanced Lectures on Machine Learning: ML Summer Schools 2003, Canberra, Australia, February 2 - 14, 2003, Tübingen, Germany, August 4 - 16, 2003, Revised Lectures}\n}

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\n \n\n \n \n Magin, T., E.; and Degrez, G.\n\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\n Journal of Computational Physics, 198(2): 424-449. 8 2004.\n \n\n\n\n
\n\n\n\n \n \n $\"Transport$ 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{\n title = {Transport algorithms for partially ionized and unmagnetized plasmas},\n type = {article},\n year = {2004},\n keywords = {Diffusion,Iterative methods,Krylov subspaces,Partially ionized mixtures,Transport coefficients,Unmagnetized plasmas},\n pages = {424-449},\n volume = {198},\n month = {8},\n publisher = {Academic Press},\n day = {10},\n id = {bf414e1a-a5a7-3c7d-95e3-af02607388f3},\n created = {2022-06-08T19:24:25.713Z},\n accessed = {2022-06-08},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-06-08T19:24:26.457Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {magin:jcp:2004},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Magin, Thierry E. and Degrez, Gérard},\n doi = {10.1016/J.JCP.2004.01.012},\n journal = {Journal of Computational Physics},\n number = {2}\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. 8 2004.\n \n\n\n\n
\n\n\n\n \n \n $\"Studies$ Paper\n \n \n \n $\"Studies$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\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{\n title = {Studies in Molecular Dynamics. I. General Method},\n type = {article},\n year = {2004},\n pages = {459},\n volume = {31},\n websites = {https://aip.scitation.org/doi/abs/10.1063/1.1730376},\n month = {8},\n publisher = {American Institute of PhysicsAIP},\n day = {6},\n id = {8beb526b-7891-37e6-a98a-dc13813a9a37},\n created = {2022-06-09T14:37:24.622Z},\n accessed = {2022-06-09},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-06-09T14:37:25.339Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {alder:jcp:2004},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Alder, B. J. and Wainwright, T. E.},\n doi = {10.1063/1.1730376},\n journal = {The Journal of Chemical Physics},\n number = {2}\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 \n Aero-optics effects testing in AEDC wind tunnels.\n \n \n \n \n\n\n \n\n\n\n In AIAA 2004-2499, 2004. \n \n\n\n\n
\n\n\n\n \n \n $\"Aero-optics$ 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

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@inproceedings{\n title = {Aero-optics effects testing in AEDC wind tunnels},\n type = {inproceedings},\n year = {2004},\n id = {202e3417-7b6e-39c7-903a-4271d07fb21c},\n created = {2022-11-07T22:28:01.908Z},\n accessed = {2022-11-07},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-11-07T22:28:02.506Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {plemmons:aiaa:2004},\n private_publication = {false},\n abstract = {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 bibtype = {inproceedings},\n author = {Plemmons, David and Feather, Brian and Baxter, Lance and Wilson, Robert and Jumper, Eric},\n doi = {10.2514/6.2004-2499},\n booktitle = {AIAA 2004-2499}\n}

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\n \n 2003\n \n \n (3)\n \n \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 \n\n\n\n
\n\n\n\n \n \n $\"The$ 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

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@article{\n title = {The role of arithmetic structure in the transition from arithmetic to algebra},\n type = {article},\n year = {2003},\n pages = {122-137},\n volume = {15},\n publisher = {Springer},\n id = {c37cc0ae-e915-33ac-b3fb-edcf611ec3e9},\n created = {2021-07-23T18:51:08.056Z},\n accessed = {2021-07-23},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-07-23T21:07:17.358Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {warren:merj:2003},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Warren, Elizabeth},\n doi = {10.1007/BF03217374},\n journal = {Mathematics Education Research Journal 2003 15:2},\n number = {2}\n}

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\n \n\n \n \n Ge, W.; and Li, J.\n\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\n Chemical Engineering Science, 58(8): 1565-1585. 4 2003.\n \n\n\n\n
\n\n\n\n \n \n $\"Macro-scale$ 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{\n title = {Macro-scale phenomena reproduced in microscopic systems—pseudo-particle modeling of fluidization},\n type = {article},\n year = {2003},\n keywords = {Dynamic simulation,Fluidization,Multi-scale,Particle method,Scale-up,Transport process},\n pages = {1565-1585},\n volume = {58},\n month = {4},\n publisher = {Pergamon},\n day = {1},\n id = {21841ce3-5338-36cf-aa1b-8390438b6809},\n created = {2022-06-09T14:42:11.989Z},\n accessed = {2022-06-09},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-06-09T14:42:12.753Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {ge:ces:2003},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Ge, Wei and Li, Jinghai},\n doi = {10.1016/S0009-2509(02)00673-5},\n journal = {Chemical Engineering Science},\n number = {8}\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 16th AIAA Computational Fluid Dynamics Conference, 2003. AIAA Paper 2003-3986\n \n\n\n\n
\n\n\n\n \n \n $\"Revisiting$ 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

@inproceedings{\n title = {Revisiting the least-squares procedure for gradient reconstruction on unstructured meshes},\n type = {inproceedings},\n year = {2003},\n publisher = {AIAA Paper 2003-3986},\n id = {193b8228-8f76-3d8e-a0f5-42f4c663057d},\n created = {2022-09-16T22:28:10.266Z},\n accessed = {2022-09-16},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-09-26T19:17:55.610Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {mavriplis:aiaa:2003},\n private_publication = {false},\n abstract = {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 bibtype = {inproceedings},\n author = {Mavriplis, Dimitri J.},\n doi = {10.2514/6.2003-3986},\n booktitle = {16th AIAA Computational Fluid Dynamics Conference}\n}

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\n \n 2002\n \n \n (2)\n \n \n

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\n \n \n

\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 NASA Glenn Research Center, 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

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@techreport{\n title = {NASA Glenn Coefficients for Calculating Thermodynamic Properties of Individual Species},\n type = {techreport},\n year = {2002},\n issue = {NASA/TP-2002-211556},\n city = {Cleveland, Ohio},\n institution = {NASA Glenn Research Center},\n id = {2190618d-a4ca-324f-b550-d57a0fb1e91e},\n created = {2021-08-31T00:24:43.577Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-08-31T00:24:43.577Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {mcbride:nasa:2002},\n source_type = {techreport},\n private_publication = {false},\n bibtype = {techreport},\n author = {McBride, Bonnie J and Zehe, Michael J and Gordon, Sanford}\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 Proceedings of the First European Workshop, Structural Health Monitoring 2002, 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{\n title = {Computational and Experimental Validation Enabling a Viable In-Flight Structural Health Monitoring Technology},\n type = {inproceedings},\n year = {2002},\n id = {714bf8bc-6adf-3de6-a518-10d6b95a62ea},\n created = {2021-11-06T18:17:57.938Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-11-06T18:17:57.938Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {shkarayev:shm:2002},\n private_publication = {false},\n bibtype = {inproceedings},\n author = {Shkarayev, S. and Raman, A. and Tessler, A.},\n booktitle = {Proceedings of the First European Workshop, Structural Health Monitoring 2002}\n}

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\n \n 2001\n \n \n (5)\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 $\"Multidisciplinary$ 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

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@article{\n title = {Multidisciplinary Optimization of Airbreathing Hypersonic Vehicles},\n type = {article},\n year = {2001},\n volume = {17},\n id = {1aedb66a-d1ac-3e35-8626-fe97a57818f9},\n created = {2021-02-17T23:42:07.027Z},\n accessed = {2021-02-17},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-02-17T23:42:08.851Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {bowcutt:jpp:2001},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Bowcutt, Kevin G},\n doi = {10.2514/2.5893},\n journal = {Journal of Propulsion and Power},\n number = {6}\n}

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\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 $\"Multidisciplinary$ Paper\n \n \n \n $\"Multidisciplinary$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\n \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{\n title = {Multidisciplinary Optimization of Airbreathing Hypersonic Vehicles},\n type = {article},\n year = {2001},\n volume = {17},\n websites = {http://arc.aiaa.org},\n id = {a217f255-6424-388b-af02-df07c914688d},\n created = {2021-05-29T00:09:06.331Z},\n accessed = {2021-05-28},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-05-29T00:09:20.113Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {bowcutt:jpp:2001},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Bowcutt, Kevin G},\n doi = {10.2514/2.5893},\n journal = {Journal of Propulsion and Power},\n number = {6}\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 \n link\n \n \n\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{\n title = {Predictions of Ablating Hypersonic Vehicles Using an Iterative Coupled Fluid/Thermal Approach},\n type = {article},\n year = {2001},\n pages = {129-139},\n volume = {15},\n id = {ce95e13c-dcee-3a81-92fe-291c60c50cfe},\n created = {2021-06-01T19:02:40.905Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-06-01T19:02:40.905Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {kuntz:jtht:2001},\n source_type = {article},\n private_publication = {false},\n bibtype = {article},\n author = {Kuntz, D W and Hassan, B and Potter, D L},\n journal = {Journal of Thermophysics and Heat Transfer},\n number = {2}\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
\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{\n title = {Low-Speed Aerodynamics},\n type = {book},\n year = {2001},\n publisher = {Cambridge University Press},\n edition = {2nd},\n id = {902ce9bf-7828-30de-acd1-d9ac89041e10},\n created = {2021-07-11T17:18:16.001Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-07-11T17:18:16.001Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {katz:2001},\n private_publication = {false},\n bibtype = {book},\n author = {Katz, Joseph and Plotkin, Allen}\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 Structural Health Monitoring: The Demands and Challenges, Proceedings of the 3rd International Workshop on Structural Health Monitoring, 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{\n title = {An Inverse Interpolation Method Utilizing In-Flight Strain Measurements for Determining Loads and Structural Response of Aerospace Vehicles},\n type = {inproceedings},\n year = {2001},\n id = {34cdb679-7b64-3e28-a03d-bb00a10b1e62},\n created = {2021-11-06T18:17:57.313Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-11-06T18:17:57.313Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {shkarayev:shm:2001},\n private_publication = {false},\n bibtype = {inproceedings},\n author = {Shkarayev, S. and Krashanitsa, R. and Tessler, A.},\n booktitle = {Structural Health Monitoring: The Demands and Challenges, Proceedings of the 3rd International Workshop on Structural Health Monitoring}\n}

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\n \n 2000\n \n \n (7)\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 \n link\n \n \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{\n title = {Temperature Dependence of Polarizability of Diatomic Homonuclear Molecules},\n type = {article},\n year = {2000},\n pages = {44-48},\n volume = {89},\n id = {63abd2f5-359c-3e18-8eb8-edb906636889},\n created = {2021-05-31T20:15:13.553Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-05-31T20:15:13.553Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {buldakov:ms:2000},\n source_type = {article},\n private_publication = {false},\n bibtype = {article},\n author = {Buldakov, M A and Matrosov, I I and Cherepanov, V N},\n journal = {Molecular Spectroscopy},\n number = {1}\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 31st AIAA Plasmadynamics and Lasers Conference, 2000. \n \n\n\n\n
\n\n\n\n \n \n $\"Near-and$ Paper\n \n \n \n $\"Near-and$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\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{\n title = {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 type = {inproceedings},\n year = {2000},\n websites = {http://arc.aiaa.org},\n id = {1e371590-cfec-3ed2-a5af-50974f0cb285},\n created = {2021-07-12T09:08:55.553Z},\n accessed = {2021-07-12},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-07-12T09:09:19.782Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {yanta:plc:2000},\n private_publication = {false},\n abstract = {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 bibtype = {inproceedings},\n author = {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 doi = {10.2514/6.2000-2357},\n booktitle = {31st AIAA Plasmadynamics and Lasers Conference}\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 \n School transitions: beginning of the end or a new beginning?.\n \n \n \n \n\n\n \n\n\n\n International Journal of Educational Research, 33(4): 325-339. 2000.\n \n\n\n\n
\n\n\n\n \n \n $\"School$ 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

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@article{\n title = {School transitions: beginning of the end or a new beginning?},\n type = {article},\n year = {2000},\n pages = {325-339},\n volume = {33},\n publisher = {Pergamon},\n id = {70ba615a-1cad-3710-98bd-ad60d00a19a6},\n created = {2021-07-23T18:27:24.669Z},\n accessed = {2021-07-23},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-07-23T18:27:26.784Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {anderson:ijer:2000},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Anderson, Lorin W. and Jacobs, Jacque and Schramm, Susan and Splittgerber, Fred},\n doi = {10.1016/S0883-0355(00)00020-3},\n journal = {International Journal of Educational Research},\n number = {4}\n}

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\n \n\n \n \n Martin, M., P.; Piomelli, U.; Candler, G., V.; and Hussaini, M., Y.\n\n\n \n \n \n \n \n Theoretical and Computational Subgrid-Scale Models for Compressible Large-Eddy Simulations.\n \n \n \n \n\n\n \n\n\n\n Theoretical and Computational Fluid Dynamics, 13: 361-376. 2000.\n \n\n\n\n
\n\n\n\n \n \n $\"Theoretical$ Paper\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

@article{\n title = {Theoretical and Computational Subgrid-Scale Models for Compressible Large-Eddy Simulations},\n type = {article},\n year = {2000},\n pages = {361-376},\n volume = {13},\n id = {dcb298db-704c-3a8a-848b-a4880208ba5b},\n created = {2021-11-12T22:46:11.790Z},\n file_attached = {true},\n profile_id = {15c6efe6-d11c-392c-a9aa-541c422eff37},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-11-12T22:53:05.888Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {martin:tcf:2000},\n private_publication = {false},\n abstract = {An a priori study of subgrid-scale (SGS) models for the unclosed terms in the energy equation is carried out using the flow field obtained from the direct simulation of homogeneous isotropic turbulence. Scale-similar models involve multiple filtering operations to identify the smallest resolved scales that have been shown to be the most active in the interaction with the unresolved SGSs. In the present study these models are found to give more accurate prediction of the SGS stresses and heat fluxes than eddy-viscosity and eddy-diffusivity models, as well as improved predictions of the SGS turbulent diffusion, SGS viscous dissipation, and SGS viscous diffusion.},\n bibtype = {article},\n author = {Martin, M. P. and Piomelli, U. and Candler, G. V. and Hussaini, M Y},\n journal = {Theoretical and Computational Fluid Dynamics}\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. 5 2000.\n \n\n\n\n
\n\n\n\n \n \n $\"Model$ Paper\n \n \n \n $\"Model$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\n \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{\n title = {Model for Heterogeneous Catalysis on Metal Surfaces with Applications to Hypersonic Flows},\n type = {article},\n year = {2000},\n keywords = {Activation Energy,Boltzmann Constant,Freestream Conditions,Heterogeneous Catalysis,Heterogeneous Chemical Kinetics,Hypersonic Flows,Melting Points,Numerical Simulation,Thermal Protection System,Wind Tunnel Tests},\n pages = {412-420},\n volume = {14},\n websites = {https://arc.aiaa.org/doi/abs/10.2514/2.6539},\n month = {5},\n publisher = {AIAA},\n day = {23},\n id = {2aaa1c01-91d9-34d2-89c3-e7c207833298},\n created = {2022-06-07T16:03:57.537Z},\n accessed = {2022-06-07},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-06-07T16:03:58.237Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {barbato:jtht:2000},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Barbato, M. and Reggiani, S. and Bruno, C. and Muylaert, J.},\n doi = {10.2514/2.6539},\n journal = {Journal of Thermophysics and Heat Transfer},\n number = {3}\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. 4 2000.\n \n\n\n\n
\n\n\n\n \n \n $\"Monte$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\n \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{\n title = {Monte Carlo analysis of macroscopic fluctuations in a rarefied hypersonic flow around a cylinder},\n type = {article},\n year = {2000},\n keywords = {Knudsen flow,Mach number,Monte Carlo methods,flow instability,flow simulation,fluctuations,hypersonic flow,rarefied fluid dynamics,vortices,wakes},\n pages = {1226},\n volume = {12},\n websites = {https://aip.scitation.org/doi/abs/10.1063/1.870372},\n month = {4},\n publisher = {American Institute of PhysicsAIP},\n day = {13},\n id = {11c32d1c-820c-3b3f-b676-47765e55e5fd},\n created = {2022-06-13T17:36:30.244Z},\n accessed = {2022-06-13},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-06-13T17:36:30.244Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {stefanov:pf:2000},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Stefanov, Stefan K. and Boyd, Iain D. and Cai, Chun Pei},\n doi = {10.1063/1.870372},\n journal = {Physics of Fluids},\n number = {5}\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 \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\n In AIAA 2000-2357, pages 19-22, 2000. \n \n\n\n\n
\n\n\n\n \n \n $\"Near-$ 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

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@inproceedings{\n title = {Near- and farfield measurements of aero-optical effects due to propagation through hypersonic flows},\n type = {inproceedings},\n year = {2000},\n pages = {19-22},\n id = {54759d67-559d-3125-8463-aab9915d9eb0},\n created = {2022-11-07T22:27:05.732Z},\n accessed = {2022-11-07},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-11-07T22:27:06.359Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {yanta:aiaa:2000},\n private_publication = {false},\n abstract = {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 bibtype = {inproceedings},\n author = {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 doi = {10.2514/6.2000-2357},\n booktitle = {AIAA 2000-2357}\n}

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\n \n 1999\n \n \n (2)\n \n \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

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@article{\n title = {Planetary-Entry Gas Dynamics},\n type = {article},\n year = {1999},\n volume = {31},\n id = {92f6ad7f-76a7-3792-97a6-29b6e410c6cf},\n created = {2021-10-25T19:31:21.683Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-10-25T19:31:21.683Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {gnoffo:arfm:1999},\n source_type = {article},\n private_publication = {false},\n bibtype = {article},\n author = {Gnoffo, Peter A},\n doi = {10.1146/annurev.fluid.31.1.459},\n journal = {Annual Review of Fluid Mechanics}\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). 5 1999.\n \n\n\n\n
\n\n\n\n \n \n $\"A$ Paper\n \n \n \n $\"A$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\n \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

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@article{\n title = {A new approach to model and simulate numerically surface chemistry in rarefied flows},\n type = {article},\n year = {1999},\n keywords = {Laplace transforms,catalysis,chemical equilibrium,chemically reactive flow,chemisorption,nonequilibrium flow,numerical analysis,rarefied fluid dynamics,surface chemistry},\n volume = {11},\n websites = {https://aip.scitation.org/doi/abs/10.1063/1.870025},\n month = {5},\n publisher = {American Institute of PhysicsAIP},\n day = {5},\n id = {5b295d30-e51c-34a2-867c-074d7db58d3b},\n created = {2022-06-09T14:34:20.895Z},\n accessed = {2022-06-09},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-06-09T14:34:21.773Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {choquet:pof:1999},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Choquet, Isabelle},\n doi = {10.1063/1.870025},\n journal = {Physics of Fluids},\n number = {6}\n}

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\n \n 1998\n \n \n (7)\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 \n Robust and efficient Cartesian mesh generation for component-based geometry.\n \n \n \n \n\n\n \n\n\n\n AIAA Journal, 36(6): 952-960. 5 1998.\n \n\n\n\n
\n\n\n\n \n \n $\"Robust$ 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 \n \n \n \n \n\n\n\n

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@article{\n title = {Robust and efficient Cartesian mesh generation for component-based geometry},\n type = {article},\n year = {1998},\n keywords = {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 pages = {952-960},\n volume = {36},\n month = {5},\n publisher = {American Institute of Aeronautics and Astronautics Inc.},\n day = {17},\n id = {35e8e453-e1e3-34f6-af89-0240163419b7},\n created = {2021-02-17T23:17:25.999Z},\n accessed = {2021-02-17},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-02-17T23:19:31.039Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {aftosmis:aj:1998},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Aftosmis, M. J. and Berger, M. J. and Melton, J. E.},\n doi = {10.2514/2.464},\n journal = {AIAA Journal},\n number = {6}\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 $\"Load$ Paper\n \n \n \n $\"Load$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\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{\n title = {Load Oscillations Caused by Unstart of Hypersonic Wind Tunnels and Engines},\n type = {article},\n year = {1998},\n volume = {14},\n websites = {http://arc.aiaa.org},\n id = {ac184be3-a5c2-3750-9578-eca1a89e8ce4},\n created = {2021-05-31T23:14:20.156Z},\n accessed = {2021-05-31},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-05-31T23:14:24.983Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {shimura:jpp:1998},\n private_publication = {false},\n abstract = {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, ProbXAC 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 bibtype = {article},\n author = {Shimura, Takashi and Mitani, Tohru and Sakuranaka, Noboru and Izumikawa, Muneo},\n doi = {10.2514/2.5287},\n journal = {Journal of Propulsion and Power},\n number = {3}\n}

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\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

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@article{\n title = {Vibrational Energy Transfer Rates Using a Forced Harmonic Oscillator Model},\n type = {article},\n year = {1998},\n pages = {57-65},\n volume = {12},\n id = {8d7a5616-0090-3668-b1a2-c1a8fbfce015},\n created = {2021-06-25T05:52:15.376Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-06-25T05:52:15.376Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {adamovich:jtht:1998},\n source_type = {article},\n private_publication = {false},\n bibtype = {article},\n author = {Adamovich, Igor V and Macheret, Sergery O and Rich, J William and Treanor, Charles E},\n journal = {Journal of Thermophysics and Heat Transfer},\n number = {1}\n}

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\n \n\n \n \n Cao, X.; Sugiyama, Y.; and Mitsui, Y.\n\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\n Computers & Structures, 69(1): 63-78. 10 1998.\n \n\n\n\n
\n\n\n\n \n \n $\"Application$ 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

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@article{\n title = {Application of artificial neural networks to load identification},\n type = {article},\n year = {1998},\n keywords = {Artificial neural network,Inverse problem,Load identification},\n pages = {63-78},\n volume = {69},\n month = {10},\n publisher = {Pergamon},\n day = {1},\n id = {6c7709d3-926e-3532-9f38-0360e98d000b},\n created = {2021-11-06T18:18:00.134Z},\n accessed = {2021-11-06},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-11-06T18:18:03.510Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {cao:cs:1998},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Cao, X. and Sugiyama, Y. and Mitsui, Y.},\n doi = {10.1016/S0045-7949(98)00085-6},\n journal = {Computers & Structures},\n number = {1}\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 Computational Methods for Solution of Inverse Problems in Mechanics. Olson, L., G.; and Saigal, S., editor(s). ASME, 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

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@inbook{\n type = {inbook},\n year = {1998},\n publisher = {ASME},\n city = {New York},\n id = {fa3a1dd5-8790-372e-ba22-c8c663c392e7},\n created = {2021-11-06T18:18:01.845Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-11-06T18:18:01.845Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {okuma:1998},\n private_publication = {false},\n bibtype = {inbook},\n author = {Okuma, M. and Oho, T.},\n editor = {Olson, L. G. and Saigal, S.},\n chapter = {Experimental Spatial Matrix Identification as a Practical Inverse Problem in Mechanics},\n title = {Computational Methods for Solution of Inverse Problems in Mechanics}\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 7th AIAA/ASME Joint Thermophysicsand Heat Transfer Conference, 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

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@inproceedings{\n title = {Multi-Component Diffusion with Application To Computational Aerothermodynamics},\n type = {inproceedings},\n year = {1998},\n publisher = {AIAA Paper 1998-2575},\n city = {Albuquerque, NM},\n id = {827f6849-afff-3096-8003-79a9d1d50231},\n created = {2022-04-18T22:09:39.831Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-04-18T22:09:39.831Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {sutton:aiaa:1998},\n source_type = {inproceedings},\n private_publication = {false},\n bibtype = {inproceedings},\n author = {Sutton, Kenneth and Gnoffo, Peter A},\n booktitle = {7th AIAA/ASME Joint Thermophysicsand Heat Transfer Conference}\n}

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\n \n\n \n \n Schwenke, D., W.\n\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\n The Journal of Chemical Physics, 89(4): 2076. 8 1998.\n \n\n\n\n
\n\n\n\n \n \n $\"Calculations$ 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 \n \n \n \n \n \n \n\n\n\n

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@article{\n title = {Calculations of rate constants for the three‐body recombination of H2 in the presence of H2},\n type = {article},\n year = {1998},\n keywords = {CHEMICAL REACTION KINETICS,COMBUSTION,ENERGY TRANSFER,HIGH TEMPERATURE,HYDROGEN,LOW TEMPERATURE,MEDIUM TEMPERATURE,POTENTIALS,RECOMBINATION,ULTRAHIGH TEMPERATURE,VERY HIGH TEMPERATURE},\n pages = {2076},\n volume = {89},\n month = {8},\n publisher = {American Institute of PhysicsAIP},\n day = {31},\n id = {8571ceb4-0b8a-3556-bff6-61678b7d00cc},\n created = {2022-09-26T18:48:12.131Z},\n accessed = {2022-09-26},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-09-26T18:48:12.677Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {schwenke:jcp:1998},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Schwenke, David W.},\n doi = {10.1063/1.455104},\n journal = {The Journal of Chemical Physics},\n number = {4}\n}

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\n \n 1997\n \n \n (3)\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 $\"Enthalpy$ Paper\n \n \n \n $\"Enthalpy$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\n \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{\n title = {Enthalpy Effects on Hypervelocity Boundary-Layer Transition: Ground Test and Flight Data},\n type = {article},\n year = {1997},\n volume = {34},\n websites = {http://arc.aiaa.org},\n id = {e9ad45f2-f68a-3062-9b55-2a904325a185},\n created = {2021-02-25T05:08:30.957Z},\n accessed = {2021-02-24},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-02-25T05:08:33.747Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {adam:jsr:1997},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Adam, Philippe H and Hornung, Hans G},\n doi = {10.2514/2.3278},\n journal = {Journal of Spacecraft and Rockets},\n number = {5}\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. 6 1997.\n \n\n\n\n
\n\n\n\n \n \n $\"Compressible$ Paper\n \n \n \n $\"Compressible$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\n \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{\n title = {Compressible Turbulence},\n type = {article},\n year = {1997},\n keywords = {Subject headings,hydrodynamics È turbulence},\n pages = {827},\n volume = {482},\n websites = {https://iopscience.iop.org/article/10.1086/304175,https://iopscience.iop.org/article/10.1086/304175/meta},\n month = {6},\n publisher = {IOP Publishing},\n day = {20},\n id = {f8aca52d-5e18-3dc4-86ec-7b8b6f69ef01},\n created = {2021-10-22T22:46:29.224Z},\n accessed = {2021-10-22},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-10-22T22:46:29.680Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {canuto:aj:1997},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Canuto, V. M.},\n doi = {10.1086/304175},\n journal = {The Astrophysical Journal},\n number = {2}\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

\n\n\n

\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 NATO Advisory Group for Aerospace Research and Development Rept. AGARD-R-808, 1997.\n \n\n\n\n
\n\n\n\n \n \n $\"Blunt$ Website\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{\n title = {Blunt Body Dynamic Derivatives},\n type = {techreport},\n year = {1997},\n websites = {http://www.dtic.mil/ docs/citations/ADA326819.},\n institution = {NATO Advisory Group for Aerospace Research and Development Rept. AGARD-R-808},\n id = {3eeb12fa-6b22-3a10-95a4-668d4badf28e},\n created = {2022-06-21T15:43:56.456Z},\n accessed = {2022-06-21},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-06-21T15:43:56.456Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {baillion:nato:97},\n private_publication = {false},\n bibtype = {techreport},\n author = {Baillion, M.}\n}

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\n

\n \n 1996\n \n \n (3)\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 $\"Quasisteady$ Paper\n \n \n \n $\"Quasisteady$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\n \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{\n title = {Quasisteady Aerodynamics for Flutter Analysis Using Steady Computational Fluid Dynamics Calculations},\n type = {article},\n year = {1996},\n volume = {33},\n websites = {http://arc.aiaa.org},\n id = {308866d5-1697-3a2e-a0ba-4c1ca628868a},\n created = {2021-10-26T17:51:19.601Z},\n accessed = {2021-10-26},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-10-26T17:51:20.191Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {scott:ja:1996},\n private_publication = {false},\n abstract = {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^lV^ k = reduced frequency, a)b/V x p = pressure q = dynamic pressure, ip^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 </>j = yth mode shape function <l>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 bibtype = {article},\n author = {Scott, Robert C and Pototzkyt, Anthony S},\n doi = {10.2514/3.46921},\n journal = {Journal of Aircraft},\n number = {1}\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^lV^ k = reduced frequency, a)b/V x p = pressure q = dynamic pressure, ip^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 j = yth mode shape function 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

\n\n\n

\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 \n\n\n\n
\n\n\n\n \n \n $\"Analysis$ Paper\n \n \n \n $\"Analysis$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\n \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{\n title = {Analysis of phenomenological models describing the catalytic properties of high-temperature reusable coatings},\n type = {article},\n year = {1996},\n keywords = {Classical Mechanics,Classical and Continuum Physics,Engineering Fluid Dynamics,Fluid,and Aerodynamics},\n pages = {910-919},\n volume = {31},\n websites = {https://link.springer.com/article/10.1007/BF02030113},\n publisher = {Springer},\n id = {e58c1924-224d-3a99-9a08-2eca98a7b5ca},\n created = {2022-05-31T19:22:11.622Z},\n accessed = {2022-05-31},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-05-31T19:22:12.246Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {kovalev:fd:1996},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Kovalev, V. L. and Kolesnikov, A. F. and Krupnov, A. A. and Yakushin, M. I.},\n doi = {10.1007/BF02030113},\n journal = {Fluid Dynamics 1997 31:6},\n number = {6}\n}

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\n \n\n \n \n Nasuti, F.; Barbato, M.; and Bruno, C.\n\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\n Journal of Thermophysics and Heat Transfer, 10(1): 131-136. 5 1996.\n \n\n\n\n
\n\n\n\n \n \n $\"Material-dependent$ 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 \n \n \n \n \n\n\n\n

\n

@article{\n title = {Material-dependent catalytic recombination modeling for hypersonic flows},\n type = {article},\n year = {1996},\n keywords = {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 pages = {131-136},\n volume = {10},\n month = {5},\n publisher = {American Inst. Aeronautics and Astronautics Inc.},\n day = {23},\n id = {ad08f3b9-b0ae-3a55-9030-022cd4f188f3},\n created = {2022-06-07T19:14:44.021Z},\n accessed = {2022-06-07},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-06-07T19:14:44.816Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {nasuti:jtht:1996},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Nasuti, F. and Barbato, M. and Bruno, C.},\n doi = {10.2514/3.763},\n journal = {Journal of Thermophysics and Heat Transfer},\n number = {1}\n}

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\n\n\n\n\n\n

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\n \n 1995\n \n \n (1)\n \n \n

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\n \n \n

\n \n\n \n \n Plimpton, S.\n\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\n Journal of Computational Physics, 117(1): 1-19. 3 1995.\n \n\n\n\n
\n\n\n\n \n \n $\"Fast$ 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{\n title = {Fast Parallel Algorithms for Short-Range Molecular Dynamics},\n type = {article},\n year = {1995},\n pages = {1-19},\n volume = {117},\n month = {3},\n publisher = {Academic Press},\n day = {1},\n id = {b90b62c6-e3ba-32d4-af1a-feb55ac5da5f},\n created = {2022-06-09T15:21:15.596Z},\n accessed = {2022-06-09},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-06-09T15:21:16.320Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {plimpton:jcp:1995},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Plimpton, Steve},\n doi = {10.1006/JCPH.1995.1039},\n journal = {Journal of Computational Physics},\n number = {1}\n}

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\n\n\n\n\n\n

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\n \n 1994\n \n \n (2)\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 \n Investigation of regularization parameters and error estimating in inverse elasticity problems.\n \n \n \n \n\n\n \n\n\n\n International Journal for Numerical Methods in Engineering, 37(6): 1039-1052. 3 1994.\n \n\n\n\n
\n\n\n\n \n \n $\"Investigation$ 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{\n title = {Investigation of regularization parameters and error estimating in inverse elasticity problems},\n type = {article},\n year = {1994},\n pages = {1039-1052},\n volume = {37},\n month = {3},\n publisher = {John Wiley & Sons, Ltd},\n day = {30},\n id = {e6979fa4-072d-3f35-ab7a-4d9b39bd0a41},\n created = {2021-11-06T17:55:13.957Z},\n accessed = {2021-11-06},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-11-06T17:55:17.234Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {maniatty:nme:1994},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Maniatty, Antoinette M. and Zabaras, Nicholas J.},\n doi = {10.1002/NME.1620370610},\n journal = {International Journal for Numerical Methods in Engineering},\n number = {6}\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 NASA, 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{\n title = {Computer Program for Calculation of Complex Chemical Equilibrium Compositions and Applications},\n type = {techreport},\n year = {1994},\n issue = {NASA-RP-1311},\n institution = {NASA},\n id = {e0235185-ffd9-316f-a763-2bb2463060f2},\n created = {2022-09-14T18:15:12.413Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-09-14T18:15:12.413Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {gordon:nasa:1996},\n source_type = {techreport},\n private_publication = {false},\n bibtype = {techreport},\n author = {Gordon, S and McBride, B J}\n}

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\n

\n \n 1993\n \n \n (4)\n \n \n

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\n \n \n

\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 Proceedings of the AIAA Missile Sciences Conference, 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{\n title = {Aero-Optical Facility and Results},\n type = {inproceedings},\n year = {1993},\n id = {96a30066-c4b4-3c48-b6d1-ebbcd16a795f},\n created = {2021-07-12T09:21:34.953Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-07-12T09:21:34.953Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {holden:msc:1993},\n private_publication = {false},\n bibtype = {inproceedings},\n author = {Holden, Michael S and Craig, J. and Ratliff, A.},\n booktitle = {Proceedings of the AIAA Missile Sciences Conference}\n}

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\n\n\n\n

\n\n\n

\n \n\n \n \n Blevins, R., D.; Holehouse, I.; and Wentz, K., R.\n\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\n Journal of Aircraft, 30(6): 971-978. 5 1993.\n \n\n\n\n
\n\n\n\n \n \n $\"Thermoacoustic$ 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 \n \n \n \n \n\n\n\n

\n

@article{\n title = {Thermoacoustic loads and fatigue of hypersonic vehicle skin panels},\n type = {article},\n year = {1993},\n keywords = {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 pages = {971-978},\n volume = {30},\n month = {5},\n day = {22},\n id = {df9fa254-e09c-31c5-8e9e-af888abffddf},\n created = {2021-10-28T20:58:25.611Z},\n accessed = {2021-10-28},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-10-28T20:58:26.187Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {blevins:ja:1993},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Blevins, Robert D. and Holehouse, Ian and Wentz, Kenneth R.},\n doi = {10.2514/3.46441},\n journal = {Journal of Aircraft},\n number = {6}\n}

\n

\n\n\n\n\n\n

\n\n\n

\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 Netherlands Energy Research Foundation, 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{\n title = {Sectional prediction of s-D effects for stalled flow on rotating blades and comparison with measurements},\n type = {techreport},\n year = {1993},\n institution = {Netherlands Energy Research Foundation},\n id = {c1886f6c-9813-3441-92f8-4e31ed67c439},\n created = {2021-11-06T17:55:11.018Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-11-06T17:55:11.018Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {snel:1993},\n private_publication = {false},\n bibtype = {techreport},\n author = {Snel, H. and Houwink, R. and Bosschers, J. and Piers, W. J. and Van Bussel, G. J. W. and Bruning, A.}\n}

\n

\n\n\n\n

\n\n\n

\n \n\n \n \n Liou, M., S.; and Steffen, C., J.\n\n\n \n \n \n \n \n A New Flux Splitting Scheme.\n \n \n \n \n\n\n \n\n\n\n Journal of Computational Physics, 107(1): 23-39. 7 1993.\n \n\n\n\n
\n\n\n\n \n \n $\"A$ 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{\n title = {A New Flux Splitting Scheme},\n type = {article},\n year = {1993},\n pages = {23-39},\n volume = {107},\n month = {7},\n publisher = {Academic Press},\n day = {1},\n id = {91aa33c5-fc9f-3bbe-abd9-e53777a213f1},\n created = {2022-11-04T17:07:45.213Z},\n accessed = {2022-11-03},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-11-04T17:07:45.693Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {liou:jcp:1993},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Liou, Meng Sing and Steffen, Christopher J.},\n doi = {10.1006/JCPH.1993.1122},\n journal = {Journal of Computational Physics},\n number = {1}\n}

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\n\n\n\n\n\n

\n

\n \n 1992\n \n \n (2)\n \n \n

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\n \n \n

\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 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

\n

@inbook{\n type = {inbook},\n year = {1992},\n pages = {175-250},\n volume = {2},\n publisher = {Birkhauser},\n chapter = {Advances in Hypersonics: Modeling Hypersonic Flows},\n id = {d034ae15-4a77-3bf9-96a2-debef80109a3},\n created = {2022-04-18T20:59:34.802Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-04-18T20:59:34.802Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {scott:1992},\n source_type = {inbook},\n private_publication = {false},\n bibtype = {inbook},\n author = {Scott, C D}\n}

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\n\n\n\n

\n\n\n

\n \n\n \n \n Holden, M., S.\n\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\n Technical Report AD-A253 792, 1992.\n \n\n\n\n
\n\n\n\n \n \n $\"A$ 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

@techreport{\n title = {A Preliminary Study Associated with the Experimental Measurement of the Aero-Optic Characteristics of Hypersonic Configurations},\n type = {techreport},\n year = {1992},\n institution = {AD-A253 792},\n id = {1d31a38f-29b8-3174-a6eb-79bfcd3fab2b},\n created = {2022-11-07T22:15:19.724Z},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-11-07T22:15:20.260Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {holden:ad:92},\n private_publication = {false},\n bibtype = {techreport},\n author = {Holden, M. S.}\n}

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\n

\n \n 1991\n \n \n (1)\n \n \n

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\n \n \n

\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

\n

@article{\n title = {Computation of Weakly Ionized Hypersonic Flows in Thermochemical Nonequilibrium},\n type = {article},\n year = {1991},\n pages = {266-273},\n volume = {5},\n id = {71fdb041-4c1d-3f39-a81c-fe4c87e55135},\n created = {2021-07-11T20:30:56.512Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-07-11T20:30:56.512Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {candler:jtht:1991},\n source_type = {article},\n private_publication = {false},\n bibtype = {article},\n author = {Candler, Graham V and MacCormack, Robert W},\n journal = {Journal of Thermophysics and Heat Transfer},\n number = {3}\n}

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\n \n 1990\n \n \n (5)\n \n \n

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\n \n \n

\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, 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

\n

@book{\n title = {Nonequilbrium Hypersonic Aerothermodynamics},\n type = {book},\n year = {1990},\n publisher = {Wiley},\n city = {New York},\n id = {aa1c29d2-451c-3795-bb3f-19dffdb84cb4},\n created = {2021-05-29T00:16:47.177Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-05-29T00:16:47.177Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {park:1990},\n source_type = {book},\n private_publication = {false},\n bibtype = {book},\n author = {Park, C}\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 \n\n\n\n
\n\n\n\n \n \n $\"Interferometric$ 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

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@article{\n title = {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 type = {article},\n year = {1990},\n pages = {803-817},\n volume = {69},\n publisher = {Taylor & Francis Group},\n id = {7ec7dc02-ea8a-3a1f-8224-2aa52d23979d},\n created = {2021-06-23T21:33:56.399Z},\n accessed = {2021-06-23},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-11-17T04:25:48.027Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {kerl:mp:1990},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Kerl, Klaus},\n doi = {10.1080/00268979000100611},\n journal = {Molecular Physics},\n number = {5}\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 \n\n\n\n
\n\n\n\n \n \n $\"Interferometric$ 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{\n title = {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 type = {article},\n year = {1990},\n pages = {803-817},\n volume = {69},\n publisher = {Taylor & Francis Group},\n id = {1d5b86ab-2bc5-3b9e-bb8f-5b033f579e8d},\n created = {2021-06-23T21:33:56.401Z},\n accessed = {2021-06-23},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-07-12T10:41:10.836Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {kerl:mp:1990},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Kerl, Klaus},\n doi = {10.1080/00268979000100611},\n journal = {Molecular Physics},\n number = {5}\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 Instability and Transition, pages 217-232, 1990. Springer, New York, NY\n \n\n\n\n
\n\n\n\n \n \n $\"Notes$ Paper\n \n \n \n $\"Notes$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\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{\n title = {Notes on Initial Disturbance Fields for the Transition Problem},\n type = {inproceedings},\n year = {1990},\n pages = {217-232},\n websites = {https://link.springer.com/chapter/10.1007/978-1-4612-3430-2_28},\n publisher = {Springer, New York, NY},\n id = {7bc1a3ff-69bc-3106-8da5-0c746cd3e3a2},\n created = {2022-01-18T03:05:47.381Z},\n accessed = {2022-01-17},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-01-18T03:05:47.919Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {bushnell:it:1990},\n private_publication = {false},\n abstract = {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 $e^N$ 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 bibtype = {inproceedings},\n author = {Bushnell, Dennis},\n doi = {10.1007/978-1-4612-3430-2_28},\n booktitle = {Instability and Transition}\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 \n Computational fluid dynamics capability for the solid-fuel ramjet projectile.\n \n \n \n \n\n\n \n\n\n\n Journal of Propulsion, 6(3): 256-262. 5 1990.\n \n\n\n\n
\n\n\n\n \n \n $\"Computational$ 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 \n \n \n \n \n\n\n\n

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@article{\n title = {Computational fluid dynamics capability for the solid-fuel ramjet projectile},\n type = {article},\n year = {1990},\n keywords = {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 pages = {256-262},\n volume = {6},\n month = {5},\n day = {23},\n id = {94825f68-51ba-3475-a926-d41af4c14d40},\n created = {2022-11-19T02:06:37.430Z},\n accessed = {2022-11-18},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-11-19T02:06:38.055Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {nusca:jp:90},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Nusca, Michael J. and Chakravarthyt, Sukumar R. and Goldberg, Uriel C.},\n doi = {10.2514/3.25428},\n journal = {Journal of Propulsion},\n number = {3}\n}

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\n \n 1989\n \n \n (6)\n \n \n

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\n \n\n \n \n Plotkin, K., J.\n\n\n \n \n \n \n \n Review of Sonic Boom Theory.\n \n \n \n \n\n\n \n\n\n\n In AIAA 12th Aeroacoustics Conference, pages 1--37, 1989. AIAA Paper 1989-1105\n \n\n\n\n
\n\n\n\n \n \n $\"Review$ 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

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@inproceedings{\n title = {Review of Sonic Boom Theory},\n type = {inproceedings},\n year = {1989},\n pages = {1--37},\n publisher = {AIAA Paper 1989-1105},\n city = {San Antonio, TX},\n id = {3e350710-a2e5-3e77-ae85-8ddf0abcd0a2},\n created = {2020-12-30T22:32:34.560Z},\n accessed = {2020-12-30},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2020-12-30T22:32:44.012Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {plotkin:aiaa:89},\n source_type = {inproceedings},\n private_publication = {false},\n abstract = {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 bibtype = {inproceedings},\n author = {Plotkin, Kenneth J.},\n doi = {10.2514/6.1989-1105},\n booktitle = {AIAA 12th Aeroacoustics Conference}\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 Hypersonics, Volume 1: Defining the Hypersonic Environment. Bertin, J., J.; Glowinski, R.; and Periaux, J., editor(s). 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

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@inbook{\n type = {inbook},\n year = {1989},\n publisher = {Birkhauser},\n id = {5a3936c4-56aa-3537-86ab-7f5ba31b0fee},\n created = {2021-02-18T00:01:33.643Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-02-18T00:01:33.643Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {trella:1989},\n private_publication = {false},\n bibtype = {inbook},\n author = {Trella, Massimo},\n editor = {Bertin, John J. and Glowinski, R. and Periaux, J.},\n chapter = {Introduction to the Hypersonic Phenomena of Hermes},\n title = {Hypersonics, Volume 1: Defining the Hypersonic Environment}\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 \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\n Technical Report NASA Langley Research Center, 1989.\n \n\n\n\n
\n\n\n\n \n \n $\"Conservation$ 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

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@techreport{\n title = {Conservation equations and physical models for hypersonic air flows in thermal and chemical nonequilibrium},\n type = {techreport},\n year = {1989},\n issue = {NASA-TP-2867},\n city = {Hampton, Virginia},\n institution = {NASA Langley Research Center},\n id = {8b6be6cf-5b6d-3e88-868b-28bf70d23581},\n created = {2021-07-11T20:07:43.121Z},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-07-11T20:07:54.213Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {gnoffo:nasa:1989},\n source_type = {techreport},\n private_publication = {false},\n bibtype = {techreport},\n author = {Gnoffo, Peter A and Gupta, R N and Shinn, J L}\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 NASA Ames Research Center, 1989.\n \n\n\n\n
\n\n\n\n \n \n $\"Transpiration$ Paper\n \n \n \n $\"Transpiration$ Website\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{\n title = {Transpiration cooling in hypersonic flight},\n type = {techreport},\n year = {1989},\n websites = {https://ntrs.nasa.gov/citations/19900010736},\n institution = {NASA Ames Research Center},\n revision = {JIAA TR-92},\n id = {3648373a-d266-3572-a5c8-0d49d16c4825},\n created = {2021-07-22T16:14:57.048Z},\n accessed = {2021-07-21},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-07-22T16:14:59.773Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {tavella:nasa:1989},\n private_publication = {false},\n abstract = {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 bibtype = {techreport},\n author = {Tavella, Domingo and Roberts, Leonard}\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

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@article{\n title = {Solving Equations: The Transition from Arithmetic to Algebra},\n type = {article},\n year = {1989},\n pages = {19-25},\n volume = {9},\n id = {86d27873-ad40-3e9b-9882-8c84ac00a5c1},\n created = {2021-07-23T18:50:12.089Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-07-23T18:50:12.089Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {filloy:flm:1989},\n private_publication = {false},\n bibtype = {article},\n author = {Filloy, E. and Rojano, T.},\n journal = {For the Learning of Mathematics},\n number = {2}\n}

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\n \n\n \n \n Zannetti, L.\n\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\n AIAA Journal, 18(7). 1989.\n \n\n\n\n
\n\n\n\n \n \n $\"Time-Dependent$ 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

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@article{\n title = {Time-Dependent Method to Solve the Inverse Problem for Internal Flows},\n type = {article},\n year = {1989},\n volume = {18},\n id = {a4a4f596-4e49-3ace-8569-88a1ecaf4a6f},\n created = {2021-11-06T17:36:24.276Z},\n accessed = {2021-11-06},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-11-06T17:36:25.906Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {zannetti:aj:1980},\n private_publication = {false},\n abstract = {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 <£ = 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 bibtype = {article},\n author = {Zannetti, L},\n doi = {10.2514/3.50816},\n journal = {AIAA Journal},\n number = {7}\n}

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\n \n 1988\n \n \n (2)\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 \n Studies of Aerothermal Loads Generated in Regions of Shock-Shock Interaction in Hypersonic Flow.\n \n \n \n \n\n\n \n\n\n\n In AIAA 26th Aerospace Sciences Meeting, 1988. \n \n\n\n\n
\n\n\n\n \n \n $\"Studies$ 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

@inproceedings{\n title = {Studies of Aerothermal Loads Generated in Regions of Shock-Shock Interaction in Hypersonic Flow},\n type = {inproceedings},\n year = {1988},\n id = {0d513616-da26-39cf-89fd-a3e32ffd806a},\n created = {2021-10-28T20:57:13.933Z},\n accessed = {2021-10-28},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-12-12T16:36:27.763Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {holden:aiaa:1988},\n private_publication = {false},\n abstract = {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 bibtype = {inproceedings},\n author = {Holden, MS and Wieting, Ar and Moselle, JR and Wietingi, Ar and Moselle, R and Glass, C},\n doi = {10.2514/6.1988-477},\n booktitle = {AIAA 26th Aerospace Sciences Meeting}\n}

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\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

\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. 5 1988.\n \n\n\n\n
\n\n\n\n \n \n $\"Comparison$ Paper\n \n \n \n $\"Comparison$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\n \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{\n title = {Comparison of predictions and experimental data for hypersonic pitching motion stability},\n type = {article},\n year = {1988},\n keywords = {Aerodynamic Characteristics,Aerodynamic Flows,Angle of Attack,Boundary Layer Transition,Hypersonic Flight,Hypersonic Vehicles,Pitch Stability,Pressure Coefficient,Shock Layers,Wind Tunnels},\n pages = {225-233},\n volume = {25},\n websites = {https://arc.aiaa.org/doi/10.2514/3.25975},\n month = {5},\n day = {23},\n id = {4870a26a-68f1-3ef1-9d2c-f528347cff90},\n created = {2022-06-15T16:32:25.708Z},\n accessed = {2022-06-15},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-06-15T16:32:26.527Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {east:jpr:88},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {East, R. A. and Hutt, G. R.},\n doi = {10.2514/3.25975},\n journal = {Journal of Spacecraft and Rockets},\n number = {3}\n}

\n

\n\n\n\n\n\n

\n

\n \n 1987\n \n \n (1)\n \n \n

\n

\n \n \n

\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, 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

\n

@book{\n title = {Inverse Problem Theory: Methods for Data Fitting and Model Parameters Estimation},\n type = {book},\n year = {1987},\n publisher = {Elsevier},\n city = {New York},\n id = {f7ae9270-e368-3d30-825b-826f6885192a},\n created = {2021-11-06T17:55:14.595Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-11-06T17:55:14.595Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {tarantola:1987},\n private_publication = {false},\n bibtype = {book},\n author = {Tarantola, A.}\n}

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\n

\n \n 1986\n \n \n (3)\n \n \n

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\n \n \n

\n \n\n \n \n Hohm, U.; and Kerl, K.\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 Molecular Physics, 58(3): 541-550. 6 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{\n title = {Temperature dependence of mean molecular polarizability of gas molecules},\n type = {article},\n year = {1986},\n pages = {541-550},\n volume = {58},\n month = {6},\n publisher = {Taylor & Francis Group},\n day = {20},\n id = {548ca754-5785-3ec8-979e-666afeab298d},\n created = {2021-06-23T21:42:39.802Z},\n accessed = {2021-06-23},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-07-12T10:41:10.292Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {hohm:mp:1986},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Hohm, Uwe and Kerl, Klaus},\n doi = {10.1080/00268978600101351},\n journal = {Molecular Physics},\n number = {3}\n}

\n

\n\n\n\n\n\n

\n\n\n

\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. 5 1986.\n \n\n\n\n
\n\n\n\n \n \n $\"Unsteady$ Paper\n \n \n \n $\"Unsteady$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\n \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{\n title = {Unsteady embedded Newton-Busemann flow theory},\n type = {article},\n year = {1986},\n keywords = {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 pages = {129-135},\n volume = {23},\n websites = {https://arc.aiaa.org/doi/10.2514/3.25798},\n month = {5},\n day = {23},\n id = {3567b87b-43ba-3edd-8e85-d67434ccf4fa},\n created = {2022-06-15T16:33:26.881Z},\n accessed = {2022-06-15},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-06-15T16:33:27.584Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {tong:jsr:86},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Tong, Bing Gang and Hui, W. H.},\n doi = {10.2514/3.25798},\n journal = {Journal of Spacecraft and Rockets},\n number = {2}\n}

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\n\n\n\n\n\n

\n\n\n

\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{\n title = {On the vibration-rotational matrix elements for diatomic molecules},\n type = {article},\n year = {1986},\n pages = {87-111},\n volume = {36},\n id = {6241edcf-f6fd-3a43-a88c-65709ea97661},\n created = {2022-11-17T04:20:39.910Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-11-17T04:20:39.910Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {bouanich:jqsrt:1986},\n source_type = {article},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Bouanich, J.-P. and Blumenfeld, L},\n doi = {https://doi.org/10.1016/0022-4073(86)90114-7},\n journal = {Journal of Quantitative Spectroscopy and Radiative Transfer},\n number = {2}\n}

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\n\n\n\n\n\n

\n

\n \n 1983\n \n \n (2)\n \n \n

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\n \n \n

\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{\n title = {A Simple Analytical Approximation for the Potential Energy of Diatomics},\n type = {article},\n year = {1983},\n pages = {228-231},\n volume = {96},\n id = {70728fa4-300f-3958-8b46-95636a7a0cfe},\n created = {2022-11-17T04:24:01.166Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-11-17T04:24:01.166Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {dmitrieva:cpl:1983},\n source_type = {article},\n private_publication = {false},\n bibtype = {article},\n author = {Dmitrieva, I K and Zenevich, V A},\n doi = {10.1016/0009-2614(83)80496-5},\n journal = {Chemical Physics Letters},\n number = {2}\n}

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\n\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{\n title = {Higher order spectroscopic constants and ionic potentials in molecular spectroscopy},\n type = {article},\n year = {1983},\n pages = {69-90},\n volume = {105},\n id = {3106052b-0977-3483-bc1b-a719874445fa},\n created = {2022-11-17T04:24:15.157Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-11-17T04:24:15.157Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {vanhooydonk:jms:1983},\n source_type = {article},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Van Hooydonk, G},\n doi = {10.1016/0166-1280(83)80034-7},\n journal = {Journal of Molecular Structure: THEOCHEM},\n number = {1}\n}

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\n\n\n\n\n\n

\n

\n \n 1981\n \n \n (2)\n \n \n

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\n \n \n

\n \n\n \n \n Roe, P., L.\n\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\n Journal of Computational Physics, 43(2): 357-372. 10 1981.\n \n\n\n\n
\n\n\n\n \n \n $\"Approximate$ 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{\n title = {Approximate Riemann solvers, parameter vectors, and difference schemes},\n type = {article},\n year = {1981},\n pages = {357-372},\n volume = {43},\n month = {10},\n publisher = {Academic Press},\n day = {1},\n id = {66de49dc-6c85-30be-b4fb-06bb3d3f8514},\n created = {2022-11-04T17:07:40.850Z},\n accessed = {2022-11-03},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-11-04T17:07:41.820Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {roe:jcp:81},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Roe, P. L.},\n doi = {10.1016/0021-9991(81)90128-5},\n journal = {Journal of Computational Physics},\n number = {2}\n}

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\n\n\n\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 \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\n Journal of Computational Physics, 40(2): 263-293. 4 1981.\n \n\n\n\n
\n\n\n\n \n \n $\"Flux$ 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{\n title = {Flux vector splitting of the inviscid gasdynamic equations with application to finite-difference methods},\n type = {article},\n year = {1981},\n pages = {263-293},\n volume = {40},\n month = {4},\n publisher = {Academic Press},\n day = {1},\n id = {a79abcc8-7b6e-3d3d-8b2f-7ec279ee5261},\n created = {2022-11-04T17:07:42.951Z},\n accessed = {2022-11-03},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-11-04T17:07:43.553Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {steger:jcp:81},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Steger, Joseph L. and Warming, R. F.},\n doi = {10.1016/0021-9991(81)90210-2},\n journal = {Journal of Computational Physics},\n number = {2}\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 12th Rarefied Gas Dynamics International Symposium, 1980. \n \n\n\n\n
\n\n\n\n \n \n $\"Monte-Carlo$ Website\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{\n title = {Monte-Carlo simulation in an engineering context},\n type = {inproceedings},\n year = {1980},\n websites = {https://ui.adsabs.harvard.edu/abs/1981PrAA...74..239B/abstract},\n id = {331cfbb2-fa40-3cfc-92a6-0320dc4b659e},\n created = {2022-06-09T14:45:59.533Z},\n accessed = {2022-06-09},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-06-09T14:45:59.533Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {bird:rgd:1980},\n private_publication = {false},\n bibtype = {inproceedings},\n author = {Bird, G. A.},\n booktitle = {12th Rarefied Gas Dynamics International Symposium}\n}

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\n \n 1978\n \n \n (2)\n \n \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 Ph.D. Thesis, 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

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@phdthesis{\n title = {A Study of Unstable Axisymmetric Seperation in High Speed Flows},\n type = {phdthesis},\n year = {1978},\n institution = {Virginia Polytechnic Institute},\n department = {Department of Aerospace and Ocean Engineering},\n id = {721264bd-f4c4-36c3-8123-e7f4fbaf7496},\n created = {2021-07-12T05:21:20.999Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-07-12T05:21:20.999Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {kenworthy:1978},\n user_context = {Ph.D. Dissertation},\n private_publication = {false},\n bibtype = {phdthesis},\n author = {Kenworthy, M.}\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{\n title = {Matrix elements for the vibrational transitions 0 → 0 to 0 → 7 of diatomic molecules},\n type = {article},\n year = {1978},\n pages = {419-423},\n volume = {20},\n id = {d77efabc-97d5-36fd-894c-b655b7e13f9c},\n created = {2022-11-17T04:20:37.636Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-11-17T04:20:37.636Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {bouanich:jqsrt:1978},\n source_type = {article},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Bouanich, J B},\n doi = {https://doi.org/10.1016/0022-4073(78)90110-3},\n journal = {Journal of Quantitative Spectroscopy and Radiative Transfer},\n number = {4}\n}

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\n\n\n\n\n\n

\n

\n \n 1977\n \n \n (2)\n \n \n

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\n \n \n

\n \n\n \n \n Panaras, A., G.\n\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\n Technical Report von Karman Institute for Fluid Dynamics, 1977.\n \n\n\n\n
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\n

@techreport{\n title = {High Speed Unsteady Seperation about Concave Bodies - a Physical Explanation},\n type = {techreport},\n year = {1977},\n institution = {von Karman Institute for Fluid Dynamics},\n revision = {Technical Note 123},\n id = {f5804ba8-2504-34e4-99a8-cf06b034ca5d},\n created = {2021-07-12T05:16:15.460Z},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-07-12T05:17:54.488Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {panaras:vki:1977},\n private_publication = {false},\n bibtype = {techreport},\n author = {Panaras, A. G.}\n}

\n

\n\n\n\n

\n\n\n

\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, 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{\n title = {Solution of Ill-Posed Problems},\n type = {book},\n year = {1977},\n publisher = {V. H. Winston and Sons},\n city = {Washington, DC},\n id = {e89d1a45-216c-321f-8d6e-1475f0251f67},\n created = {2021-11-06T18:17:58.994Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-11-06T18:17:58.994Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {tikhonov:1977},\n private_publication = {false},\n bibtype = {book},\n author = {Tikhonov, A. N. and Arsenin, V.}\n}

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\n

\n \n 1976\n \n \n (1)\n \n \n

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\n \n \n

\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{\n title = {Dunham Potential Energy Coefficients of the Hydrogen Halides and Carbon Monoxide},\n type = {article},\n year = {1976},\n pages = {332-336},\n volume = {61},\n id = {ca81918a-8cf8-38cb-bb64-6f1186da8720},\n created = {2022-11-17T04:24:37.340Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-11-17T04:24:37.340Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {ogilvie:jms:1976},\n source_type = {article},\n private_publication = {false},\n bibtype = {article},\n author = {Ogilvie, J F and Koo, D},\n doi = {10.1016/0022-2852(76)90323-4},\n journal = {Journal of Molecular Spectroscopy},\n number = {3}\n}

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\n

\n \n 1975\n \n \n (1)\n \n \n

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\n \n \n

\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. 5 1975.\n \n\n\n\n
\n\n\n\n \n \n $\"Generalized$ Paper\n \n \n \n $\"Generalized$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\n \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{\n title = {Generalized unsteady embedded Newtonian flow},\n type = {article},\n year = {1975},\n keywords = {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 pages = {718-726},\n volume = {12},\n websites = {https://arc.aiaa.org/doi/10.2514/3.27870},\n month = {5},\n day = {23},\n id = {9c00a624-29b2-353c-8ec1-e8f084748615},\n created = {2022-06-15T16:35:08.763Z},\n accessed = {2022-06-15},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-06-15T16:35:09.425Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {ericcson:jsr:1975},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Ericsson, Lars E.},\n doi = {10.2514/3.27870},\n journal = {Journal of Spacecraft and Rockets},\n number = {12}\n}

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\n\n\n\n\n\n

\n

\n \n 1974\n \n \n (1)\n \n \n

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\n \n \n

\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 \n\n\n\n
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\n

@article{\n title = {Turbulent hypersonic viscous interaction},\n type = {article},\n year = {1974},\n pages = {145-156},\n volume = {63},\n websites = {https://doi.org/10.1017/S0022112074001054},\n publisher = {Cambridge University Press},\n id = {2d9a39c5-c02a-35a0-8ac2-f58b5bc6ceda},\n created = {2021-02-17T23:56:25.955Z},\n accessed = {2021-02-17},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-02-17T23:56:29.113Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {stollery:jfm:1974},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Stollery, J. L. and Bates, L.},\n doi = {10.1017/S0022112074001054},\n journal = {Journal of Fluid Mechanics},\n number = {1}\n}

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\n\n\n\n\n\n

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\n \n 1973\n \n \n (1)\n \n \n

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\n \n \n

\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 NASA Technical Report, 1973.\n \n\n\n\n
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\n

@techreport{\n title = {Theoretical and experimental studies of reentry plasmas},\n type = {techreport},\n year = {1973},\n websites = {https://ntrs.nasa.gov/citations/19730013358},\n institution = {NASA Technical Report},\n id = {a434e2cf-70a4-3a1a-9ef1-8c87838ee915},\n created = {2022-06-08T18:12:20.236Z},\n accessed = {2022-06-08},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-06-08T18:12:20.236Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {dunn:nasa:73},\n private_publication = {false},\n bibtype = {techreport},\n author = {Dunn, M. G. and Kang, S.}\n}

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\n\n\n\n

\n\n\n\n\n\n

\n

\n \n 1970\n \n \n (1)\n \n \n

\n

\n \n \n

\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 $\"Effects$ Paper\n \n \n \n $\"Effects$ Website\n \n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\n \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{\n title = {Effects of Flow Unsteadiness on Hypersonic Wind-Tunnel Spectroscopic Diagnostics},\n type = {article},\n year = {1970},\n volume = {8},\n websites = {http://arc.aiaa.org},\n id = {0a720f19-081f-3a31-a26b-4979bde64c39},\n created = {2021-05-31T23:14:20.146Z},\n accessed = {2021-05-31},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-05-31T23:14:23.072Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {weeks:aj:1970},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Weeks, Thomas M},\n doi = {10.2514/3.5926},\n journal = {AIAA Journal},\n number = {8}\n}

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\n\n\n\n\n\n

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\n \n 1969\n \n \n (1)\n \n \n

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\n \n \n

\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 NASA Technical Report E-2411, 1969.\n \n\n\n\n
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\n

@techreport{\n title = {Apollo Navigation, Guidance, and Control Systems: A Progress Report},\n type = {techreport},\n year = {1969},\n institution = {NASA Technical Report E-2411},\n id = {341a79ca-80b6-3c30-8a19-3fb10d3c1a08},\n created = {2022-06-20T13:40:52.201Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-06-20T13:40:52.201Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {hoag:nasa:69},\n private_publication = {false},\n bibtype = {techreport},\n author = {Hoag, D. G.}\n}

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\n \n 1968\n \n \n (1)\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
\n\n\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{\n title = {Quantitative Correlations between Rotational and Vibrational Spectroscopic Constants in Diatomic Molecules},\n type = {article},\n year = {1968},\n pages = {5399-5415},\n volume = {49},\n id = {ef62ba99-6802-3eb8-b4b3-54b7033df3d4},\n created = {2022-11-17T04:22:12.315Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-11-17T04:22:12.315Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {calder:jcp:1968},\n source_type = {article},\n private_publication = {false},\n bibtype = {article},\n author = {Calder, G V and Ruedenberg, Klaus},\n doi = {10.1063/1.1670065},\n journal = {The Journal of Chemical Physics},\n number = {12}\n}

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\n \n 1967\n \n \n (2)\n \n \n

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\n \n \n

\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. 1 1967.\n \n\n\n\n
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\n

@article{\n title = {Heat flow through a Langmuir sheath in the presence of electron emission},\n type = {article},\n year = {1967},\n pages = {85},\n volume = {9},\n websites = {https://iopscience.iop.org/article/10.1088/0032-1028/9/1/410,https://iopscience.iop.org/article/10.1088/0032-1028/9/1/410/meta},\n month = {1},\n publisher = {IOP Publishing},\n day = {1},\n id = {6e9efb48-65c4-3478-9017-ab03ebe0d317},\n created = {2021-12-01T20:22:31.444Z},\n accessed = {2021-12-01},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-12-01T20:22:32.194Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {hobbs:pp:1967},\n private_publication = {false},\n bibtype = {article},\n author = {Hobbs, G. D. and Wesson, J. A.},\n doi = {10.1088/0032-1028/9/1/410},\n journal = {Plasma Physics},\n number = {1}\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 NATO Advisory Group for Aerospace Research and Development, 1967.\n \n\n\n\n
\n\n\n\n \n \n $\"Techniques$ Website\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{\n title = {Techniques for Measurement of Dynamic Stability Derivatives in Ground Test Facilities},\n type = {techreport},\n year = {1967},\n websites = {http://www.dtic.mil/docs/citations/ AD0669227.},\n institution = {NATO Advisory Group for Aerospace Research and Development},\n id = {cdcb7676-b826-3b04-bbe3-7149ccd1fd37},\n created = {2022-06-21T15:45:58.890Z},\n accessed = {2022-06-21},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-06-21T23:24:31.886Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {schuler:nato:67},\n private_publication = {false},\n bibtype = {techreport},\n author = {Schuler, C. J. and Ward, L. K. and Hodapp, A.}\n}

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\n \n 1966\n \n \n (1)\n \n \n

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\n \n\n \n \n Sutton; and W, G.\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

\n

@book{\n title = {Direct energy conversion},\n type = {book},\n year = {1966},\n keywords = {* - 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 publisher = {McGraw-Hill Book Company},\n id = {ba2ae54d-fe40-36c9-9521-5821d69407a6},\n created = {2021-07-22T16:00:24.925Z},\n accessed = {2021-07-22},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-07-23T21:07:17.139Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {sutton:1966},\n private_publication = {false},\n bibtype = {book},\n author = {Sutton, undefined and W, G}\n}

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\n \n 1965\n \n \n (1)\n \n \n

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\n \n\n \n \n Touryan, K., J.\n\n\n \n \n \n \n \n A Hypersonic Plasma Power Generator.\n \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 $\"A$ 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{\n title = {A Hypersonic Plasma Power Generator},\n type = {article},\n year = {1965},\n volume = {3},\n id = {ad2d20a4-b7bf-33bd-9305-c8913b4805f1},\n created = {2021-04-21T23:31:48.014Z},\n accessed = {2021-04-21},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-07-23T20:58:41.084Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {touryan:aj:65},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Touryan, K J},\n doi = {10.2514/3.2942},\n journal = {AIAA Journal},\n number = {4}\n}

\n

\n\n\n\n\n\n

\n

\n \n 1964\n \n \n (3)\n \n \n

\n

\n \n \n

\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{\n title = {Thermionic Generator for Re-Entry Vehicles},\n type = {article},\n year = {1964},\n pages = {1302-1310},\n volume = {52},\n id = {fb6f84ca-74d6-3bee-9b90-6443804acbca},\n created = {2021-07-22T16:13:53.401Z},\n accessed = {2021-07-22},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-07-22T16:13:53.401Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {leblanc:ieee:1964},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Leblanc, A. R. and Grannemann, W. W.},\n doi = {10.1109/PROC.1964.3366},\n journal = {Proceedings of the IEEE},\n number = {11}\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 Sandia Laboratories, 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{\n title = {The hypersonic plasma converter II},\n type = {techreport},\n year = {1964},\n institution = {Sandia Laboratories},\n revision = {SC-RR4960},\n id = {48c5c3bd-c46e-3c32-a793-8ddfb9c1c6a0},\n created = {2021-07-22T16:13:53.548Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-07-22T16:13:53.548Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {touryan:sandia:1964},\n private_publication = {false},\n bibtype = {techreport},\n author = {Touryan, K J}\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 General Electric Missile and Space Division Technical Report R64SD22, 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{\n title = {Ionization of Cesium and Sodium Contaminated Air in the Hypersonic Slender Body Boundary Layer},\n type = {techreport},\n year = {1964},\n institution = {General Electric Missile and Space Division Technical Report R64SD22},\n id = {a3177b06-19bf-32f1-ad1d-921d44621ab8},\n created = {2022-06-08T18:15:27.438Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-06-08T18:15:27.438Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {lenard:64},\n private_publication = {false},\n bibtype = {techreport},\n author = {Lenard, M>}\n}

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\n\n\n\n

\n\n\n\n\n\n

\n

\n \n 1963\n \n \n (1)\n \n \n

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\n \n \n

\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
\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{\n title = {Systematics of Vibrational Relaxation},\n type = {article},\n year = {1963},\n pages = {98-101},\n volume = {39},\n id = {f1d94087-840a-3132-acf5-ac2e79bcc942},\n created = {2021-05-31T18:10:03.591Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-05-31T18:10:03.591Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {millikan:jcp:1963},\n source_type = {article},\n private_publication = {false},\n bibtype = {article},\n author = {Millikan, R C and White, D R},\n journal = {Journal of Chemical Physics},\n number = {1}\n}

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\n\n\n\n\n\n

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\n \n 1962\n \n \n (2)\n \n \n

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\n \n \n

\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 NASA TN D-1304, 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

\n

@techreport{\n title = {Secondary Flow-Fields Embedded in Hypersonic Shock Layers},\n type = {techreport},\n year = {1962},\n institution = {NASA TN D-1304},\n id = {801a29f1-bced-32bc-a718-3bed27afc3ea},\n created = {2022-06-15T16:37:54.373Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-06-15T16:37:54.373Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {seiff:nasa:62},\n private_publication = {false},\n bibtype = {techreport},\n author = {Seiff, A.}\n}

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\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 NASA TN-D 1148, 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

\n

@techreport{\n title = {Correlation of the Bow-Wave Profiles of Blunt Bodies},\n type = {techreport},\n year = {1962},\n institution = {NASA TN-D 1148},\n id = {e0761493-3142-38ac-9ca9-7bfa95907291},\n created = {2022-06-15T16:40:47.743Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-06-15T16:40:47.743Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {seiff:nasa:62a},\n private_publication = {false},\n bibtype = {techreport},\n author = {Seiff, A. and Whiting, E. E.}\n}

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\n\n\n\n\n\n

\n

\n \n 1961\n \n \n (2)\n \n \n

\n

\n \n \n

\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
\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{\n title = {Wave Propagation in a Turbulent Medium},\n type = {book},\n year = {1961},\n publisher = {McGraw-Hill},\n id = {b15d7534-819b-3364-b47a-e314c5de510c},\n created = {2021-05-31T18:11:36.767Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-05-31T18:11:36.767Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {tatarski:1961},\n source_type = {book},\n private_publication = {false},\n bibtype = {book},\n author = {Tatarski, V I}\n}

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\n\n\n\n

\n\n\n

\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 NASA TN D-1147, 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{\n title = {Calculation of Flow Fields from Bow- Wave Profiles for the Downstream Region of Blunt-Nosed Circular Cylinders in Axial Hypersonic Flight},\n type = {techreport},\n year = {1961},\n institution = {NASA TN D-1147},\n id = {a6f0739f-ab17-3491-bde0-1cc6c3753c15},\n created = {2022-06-15T16:39:34.838Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-06-15T16:39:34.838Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {seiff:nasa:61},\n private_publication = {false},\n bibtype = {techreport},\n author = {Seiff, A. and Whiting, E. E.}\n}

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\n\n\n\n\n\n

\n

\n \n 1960\n \n \n (1)\n \n \n

\n

\n \n \n

\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, 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{\n title = {Wave Propagation in a Random Medium},\n type = {book},\n year = {1960},\n publisher = {McGraw-Hill},\n city = {New York},\n id = {93e8fa36-295c-366a-a91a-eaae9a5ec163},\n created = {2021-05-31T18:11:36.765Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-05-31T18:11:36.765Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {chernov:1960},\n source_type = {book},\n private_publication = {false},\n bibtype = {book},\n author = {Chernov, L A}\n}

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\n

\n \n 1959\n \n \n (1)\n \n \n

\n

\n \n \n

\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 NASA, 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{\n title = {Investigation of the Flow over a Spiked-Nose Hemisphere Cylinder at a Mach Number of 6.8},\n type = {techreport},\n year = {1959},\n institution = {NASA},\n revision = {Technical Note D-118},\n id = {1788f1cd-5b8c-3a33-ac57-0a4ddb7a3238},\n created = {2021-07-12T05:21:20.996Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-07-12T05:21:20.996Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {crawford:nasa:1959},\n private_publication = {false},\n bibtype = {techreport},\n author = {Crawford, Davis H.}\n}

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\n\n\n\n\n\n

\n

\n \n 1958\n \n \n (1)\n \n \n

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\n \n \n

\n \n\n \n \n Fay, J.; and Riddell, F., R.\n\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\n Journal of the Aerospace Sciences, 25(2): 73-85. 2 1958.\n \n\n\n\n
\n\n\n\n \n \n $\"Theory$ 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 \n \n \n \n \n\n\n\n

\n

@article{\n title = {Theory of Stagnation Point Heat Transfer in Dissociated Air},\n type = {article},\n year = {1958},\n keywords = {Aerodynamics,Atomic Diffusion,Boundary Layer Equations,Heat Transfer Measurements,Hypersonic Viscous Flow,Kinematic Viscosity,Prandtl Number,Stagnation Temperature,Thermal Diffusivity,Universal Gas Constant},\n pages = {73-85},\n volume = {25},\n month = {2},\n publisher = {American Institute of Aeronautics and Astronautics (AIAA)},\n day = {30},\n id = {99f086d4-0018-3790-940c-c12386b8e672},\n created = {2021-05-28T23:42:04.580Z},\n accessed = {2021-05-28},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-07-23T21:07:17.336Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {fay:jas:1958},\n private_publication = {false},\n abstract = {applicability for this approach.},\n bibtype = {article},\n author = {Fay, J.A. and Riddell, F. R.},\n doi = {10.2514/8.7517},\n journal = {Journal of the Aerospace Sciences},\n number = {2}\n}

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\n\n\n\n\n\n

\n

\n \n 1957\n \n \n (1)\n \n \n

\n

\n \n \n

\n \n\n \n \n Lees, L.; and Kubota, T.\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 Journal of the Aeronautical Sciences, 24(3): 195-202. 3 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 \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n \n\n\n\n

\n

@article{\n title = {Inviscid Hypersonic Flow Over Blunt-Nosed Slender Bodies},\n type = {article},\n year = {1957},\n keywords = {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 pages = {195-202},\n volume = {24},\n month = {3},\n publisher = {American Institute of Aeronautics and Astronautics (AIAA)},\n day = {29},\n id = {ce273fb5-7b7c-3ab2-8dfc-3ff0c9d86e06},\n created = {2021-05-28T23:42:04.823Z},\n accessed = {2021-05-28},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-07-23T21:07:17.127Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {lees:jas:1957},\n private_publication = {false},\n bibtype = {article},\n author = {Lees, Lester and Kubota, Toshi},\n doi = {10.2514/8.3803},\n journal = {Journal of the Aeronautical Sciences},\n number = {3}\n}

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\n\n\n\n\n\n

\n

\n \n 1956\n \n \n (1)\n \n \n

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\n \n \n

\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 \n\n\n\n
\n\n\n\n \n\n \n \n doi\n \n \n\n \n link\n \n \n\n bibtex\n \n\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{\n title = {Thermionic Emission, Field Emission, and the Transition Region},\n type = {article},\n year = {1956},\n volume = {102},\n publisher = {American Physical Society},\n id = {97a0f195-d90b-3da2-8724-c50bedbd594d},\n created = {2021-07-22T15:57:13.913Z},\n accessed = {2021-07-21},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-07-22T15:57:13.913Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {murphy:pr:1956},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Murphy, E. L. and R. H. Good, Jr},\n doi = {10.1103/PhysRev.102.1464},\n journal = {Physical Review},\n number = {6}\n}

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\n \n 1955\n \n \n (1)\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, 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

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@book{\n title = {Aeroelasticity},\n type = {book},\n year = {1955},\n publisher = {Addison-Wesley},\n city = {Cambridge},\n id = {0532b9f3-0aa3-33e4-af52-b77b3117c8f8},\n created = {2021-10-26T17:48:03.162Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-10-26T17:48:03.162Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {bisplinghoff:1955},\n private_publication = {false},\n bibtype = {book},\n author = {Bisplinghoff, R. and Ashley, H. and Halfman, R.}\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). 5 1954.\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{\n title = {A Model for Collision Processes in Gases. I. Small Amplitude Processes in Charged and Neutral One-Component Systems},\n type = {article},\n year = {1954},\n volume = {94},\n month = {5},\n publisher = {American Physical Society},\n day = {1},\n id = {15f402fc-d2e3-3dd6-8b2f-f1d5de158390},\n created = {2021-07-19T20:57:24.019Z},\n accessed = {2021-07-19},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-07-19T20:57:24.019Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {bhatnagar:pr:1954},\n private_publication = {false},\n abstract = {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 bibtype = {article},\n author = {Bhatnagar, P. L. and Gross, E. P. and Krook, M.},\n doi = {10.1103/PhysRev.94.511},\n journal = {Physical Review},\n number = {3}\n}

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\n\n\n

\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 1949\n \n \n (1)\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 \n\n\n\n
\n\n\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{\n title = {Thermionic Emission},\n type = {article},\n year = {1949},\n volume = {21},\n publisher = {American Physical Society},\n id = {abdc1afb-e55b-394e-b3be-d3601860b8e1},\n created = {2021-07-22T15:57:14.124Z},\n accessed = {2021-07-21},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-07-22T15:57:14.124Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {herring:rmp:1949},\n private_publication = {false},\n bibtype = {article},\n author = {Herring, Conyers and Nichols, M. H.},\n doi = {10.1103/RevModPhys.21.185},\n journal = {Reviews of Modern Physics},\n number = {2}\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
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@article{\n title = {The Energy Levels of a Rotating Vibrator},\n type = {article},\n year = {1932},\n pages = {721-731},\n volume = {41},\n id = {fe71f78d-370a-31cc-a662-e5c8ce19b93c},\n created = {2022-11-17T04:21:58.660Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2022-11-17T04:21:58.660Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {dunham:pr:1932},\n source_type = {article},\n private_publication = {false},\n bibtype = {article},\n author = {Dunham, J L},\n journal = {Physical Review},\n number = {6}\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 \n\n\n\n
\n\n\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{\n title = {Thermionic Emission},\n type = {article},\n year = {1930},\n volume = {2},\n publisher = {American Physical Society},\n id = {534ad389-508a-36d3-b766-49339b61968a},\n created = {2021-07-22T15:57:14.118Z},\n accessed = {2021-07-21},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-07-22T15:57:14.118Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {dushman:rmp:1930},\n private_publication = {false},\n bibtype = {article},\n author = {Dushman, Saul},\n doi = {10.1103/RevModPhys.2.381},\n journal = {Reviews of Modern Physics},\n number = {4}\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

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@book{\n title = {Emission of Electricty from Hot Bodies},\n type = {book},\n year = {1921},\n publisher = {Longmans, Green, and Co.},\n id = {b8d42ff5-7560-3aa0-a374-4edc442c4265},\n created = {2021-07-22T23:13:59.823Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-07-22T23:13:59.823Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {richardson:1921},\n source_type = {book},\n private_publication = {false},\n bibtype = {book},\n author = {Richardson, O W}\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

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@article{\n title = {The Electrical Conductivity Imparted to a Vacuum by Hot Conductors},\n type = {article},\n year = {1903},\n pages = {497-549},\n volume = {201},\n id = {8fd799ce-5d4b-3011-a8aa-f5fe54fcbdb0},\n created = {2021-04-21T21:48:43.499Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-04-21T21:48:43.499Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {richardson:ptrsl:1903},\n source_type = {article},\n private_publication = {false},\n bibtype = {article},\n author = {Richardson, O W},\n journal = {Philosophical Transactions of the Royal Society of London}\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
\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{\n title = {On the negative radiation form hot platinum},\n type = {article},\n year = {1903},\n id = {0886a744-34a8-383a-83fa-5af1dc3773af},\n created = {2021-07-22T23:11:42.461Z},\n file_attached = {false},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-07-22T23:11:42.461Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {true},\n hidden = {false},\n citation_key = {richardson:pcps:1903},\n private_publication = {false},\n bibtype = {article},\n author = {Richardson, O W},\n journal = {Philosophical of the Cambridge Philosophical Society}\n}

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