As the cost of wind tunnel testing keeps escalating, much of the preliminary design of hypersonic vehicles is based on CFD. Questions posed by replacing the solution of NSE partial differential equations with algebraic sets of linearized finite volume equations (FDE) are analyzed. Besides the impact of numerics, results of CFD simulations suffer from uncertainty due to approximations of the real physics of hypersonics. This uncertainty is due to that of the physics used to simulate SCRJ combustion, including chemical kinetics data, turbulence models, and the very nature of the diagnostics used in comparing numerical results and experimental measurements. Improving physical modeling by acknowledging the importance of turbulent backscatter and of greater realism of combustion and combustion-turbulence coupling models in RANS and LES is also discussed. It is concluded that more realistic simulations are feasible, among other things, by devoting efforts and resources to solving nonlinear set of FDE.
Hypersonic Flow Simulation
sp propuls
2023-11-28
22 pages
Aufsatz/Kapitel (Buch)
Elektronische Ressource
Englisch
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