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\n  \n 2019\n \n \n (2)\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 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 \"AerothermodynamicPaper\n  \n \n\n \n \n doi\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 The objective of this study is to develop a reliable and efficient design optimization method for hypersonic vehicles focused on aerothermodynamic environments. Considering the nature of hypersonic flight, a high-fidelity aerothermodynamic analysis code is used for the simulation of weakly ionized hypersonic flows in thermochemical nonequilibrium. A gradient-based method is implemented for optimization. Bezier or nonuniform rational basis spline curves are used to parametrize the geometry or the geometry change. Linear elasticity theory is implemented for mesh deformation. Penalty functions are utilized to prevent undesired geometrical changes. The design objective is to minimize drag without increasing the total heat transfer rate and the maximum values of the surface heat flux, temperature, and pressure. Design optimizations are performed at different trajectory points of the IRV-2 vehicle. The effects of parametrizations, the number of design variables, and freestream conditions on design performance are studied.\n
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\n \n\n \n \n 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 \"ShapePaper\n  \n \n \n \"ShapeWebsite\n  \n \n\n \n \n doi\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 The objective of the current study is to designanoptimumreentry vehicle shape thatminimizes heat loading subject to constraints on themaximumvalues of surface heat flux and temperature. A new heat loading formulation is developed for objective function evaluations. Axisymmetric Navier-Stokes and finite-rate chemical reaction equations are solved to evaluate the objectiveandconstraint functions.TheMenterSSTturbulencemodel isemployedfor turbulence closure. A gradient-based method is used for optimization. The sensitivities of the objective and constraint functions are evaluated using the finite-difference method. In shape optimization, the geometry change or the geometry itself is parameterized using different numbers of nonuniform rational basis spline (NURBS) or Bezier curves. Designs are performed at different trajectory points of the IRV-2 vehicle. The effects of flight path angle and reentry velocity on the heat transfer and trajectory characteristics of the original and designed geometries are quantified.\n
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