Adjoint-Based Aerothermodynamic Shape Design of Hypersonic Vehicles in Non-Equilibrium Flows
Author:
Affiliation:
1. Stanford University
Publisher
American Institute of Aeronautics and Astronautics
Link
http://arc.aiaa.org/doi/pdf/10.2514/6.2014-0513
Reference34 articles.
1. Aero-Thermodynamics for Conceptual Design
2. Demonstration of Integrated Trajectory/Aerothermal/TPS Sizing Design Tools For Mars Smart Lander
3. Analytic Hypersonic Aerodynamics for Conceptual Design of Entry Vehicles
4. Fundamental Aeronautics Hypersonics Project: Overview
5. Computational Fluid Dynamics for Winged Re-entry Vehicles at Hypersonic Conditions
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2. Discrete Empirical Interpolation Based Hyper-Reduced Order Model for Steady Hypersonic Flows;AIAA SCITECH 2022 Forum;2022-01-03
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