Flow and Heat Flux Features for Supersonic Flow Past a Flying Vehicle Model

Numerical simulation of supersonic (M∞ = 2.5) flow of viscous heat-conducting gas past a flying vehicle model for various attack angles and wall temperatures was carried out on the basis of an unsteady Reynolds averaged Navier–Stokes equations system (URANS) with Spalart–Allmaras (SA) and Menter’s SST turbulence model as well as with the hybrid IDDES+SA method. Three-dimensional features of the flow and surface heat flux dependence on wall temperature were investigated. The dependence of the base flow on the chosen turbulence model was studied. Comparison of simulation results with experimental data was carried out.