Viscous hypersonic shock-on-shock interaction on blunt cowl lips

摘要: The effects of impinging ramp shocks on a two-dimensional viscous inlet cowl the National Aerospace Plane (NASP) or blunt body flow fields for various impingement locations are numerically simulated by recently developed second-order implicit total variation diminishing (TVD) algorithm. results demonstrate that accurate computation heat transfer rate is crucially dependent adequate normal grid resolution at wall. numerical compared with recent experimental data. Due to complex patterns occur shock-on-shock flows, adaptive procedures utilized.