Research on the application of a turbulence models with compressibility effects correction for a hypersonic vehicle

A series of numerical analyses have been performed to investigate the flow characteristics of a hypersonic vehicle model. Flow fields corresponding to the Mach number and attack angle were analyzed by solving the Reynolds averaged Navier-stokes equations with the stand k-ε turbulence model in which the compressibility effects were considered. With the correction of compressibility effects, the standard k-ε turbulence model can capture delicate shock wave structures and complex pressure variation characteristics, and their calculation results are in highly agreement. The calculated shock wave structures and pressure variation tendency agree well with experimental data, except for some differences in the variation of the static pressure on the pre-compressed surface. Compared with the original k-ε turbulence model, the improved model with compressibility effects correction obtains more accurate data, implying the validity and effectiveness of the numerical approach for analyzing relevant flow field.