Several common spatial dispersion schemes and turbulence models in current computational fluid dynamics were compared and analyzed to investigate complex flow phenomenons such as strong shock waves

shock waves/boundary layer interaction

flow separation and turbulent flow in hypersonic flight. The results demonstrate that the resolutions of strong shock waves are the same by different schemes. Roe and LDE (low diffusion E-CUSP (convective upwind split pressure)) schemes show better agreement in friction coefficient and heat transfer coefficient with experimental data than other schemes. The friction coefficient predicted by S-A (Spalart-Allmaras) turbulence model is greater than that by k-ω SST (shear stress transport) turbulence model about 10%. The separation zone of the latter is twice the size of the former and the separation point is located in front.