A method for solving the viscous hypersonic flow field around realistic configurations is presented. The numerical procedure for generating the required finite difference grid and the two-factored implicit flow solver are described. Results are presented for the shuttle orbiter and a generic wing-body configuration at hypersonic Mach numbers.
Numerical Simulation of the Hypersonic Flow Around Lifting Vehicles
1987
28 pages
Report
No indication
English
Aerodynamics , Manned Spacecraft , Aerodynamic configurations , Computational fluid dynamics , Flow distribution , Hypersonic flow , Space shuttle orbiters , Body-wing configurations , Computational grids , Digital simulation , Flux vector splitting , Navier-stokes equation , Viscous flow , Finite difference theory , Flow equations , Hyperbolic differential equations