A method of 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
11 pages
Report
No indication
English
Aerodynamics , Body-wing configurations , Computational fluid dynamics , Digital simulation , Hypersonic flow , Space shuttle orbiters , Aerodynamic configurations , Computational grids , Flow distribution , Flux vector splitting , Navier-stokes equation , Viscous flow , Finite difference theory , Flow equations , Hyperbolic differential equations