Effects of Wall Temperature on Hypersonic Impinging Shock-Wave/Turbulent-Boundary-Layer Interactions

We carry out a parametric study of hypersonic impinging shock-wave/turbulent-boundary-layer interactions (SBLIs) at hypersonic conditions (Mach number 6.0) by means of numerical simulation of the Reynolds-averaged Navier–Stokes (RANS) equations, with the eventual goal of establishing wall temperature and Reynolds number effects. Comparison with available direct numerical simulation and experimental data shows that RANS is capable of predicting the main features of SBLI, namely, typical size and distribution of the wall properties. A large number of flow cases were computed to examine the scaling of the global flow parameters over a wide range of wall temperatures and Reynolds numbers. As expected, the interaction zone is reduced as the wall is cooled, and as the Reynolds number is increased. A modified form of the scaling originally introduced by Souverein et al. [Journal of Fluid Mechanics, Vol. 714, 2013, pp. 505–535] is here considered to account for nonadiabatic wall state, which is found to successfully collapse the data to the distributions obtained for adiabatic flow, with some remaining deviations associated with lowReynolds-number effects.