Abstract: TVD scheme is one of the most advanced schemes for investigating supersonic and hypersonic complex flows in which shock wave is one of important properties up to date. In present paper, axisymmetric viscous flows about three indented nosetips and hypersonic flow about a blunt-cone body (θ=10°) at angles of attack were simulated with a two-order windward TVD scheme. High quatitive shocks and surface pressure distributions agreed with experiments and results from space-marching method were obtained. It is also demonstrated the unique advantages of present method for computing complex flows over re-entry vehicles.

Key words: flows around blunt body, TVD scheme, numerical simulation shocks