This paper evaluates a number of inviscid flux schemes for direct numerical simulations of supersonic boundary layers. Supersonic turbulent boundary layers are, by themselves, significant drivers of heating and acoustics on launch vehicles, high speed aircraft and rocket engines. Further, they are foundational to more complex turbulence problems in these aerospace applications, such as shock-turbulent boundary layer interactions and supersonic film cooling. Hence it is important to validate numerical methods for this type of flow as a building block for more complicated situations. A temporally-developing boundary layer approach is utilized, with an adiabatic wall assumption. Freestream conditions ranging from effectively incompressible to hypersonic are evaluated. The inviscid flux schemes are compared with respect to stability, boundary layer skin friction, mean velocity profile, shape factor and recovery factor. The influence of grid resolution on these characteristics is also evaluated.
展开▼
