Hypersonic Shock Wave/Turbulent Boundary Layer Interaction over a Compression Ramp

A parametric study of ramp-induced planar shock-wave/turbulent-boundary-layer interactions (SBLIs) is carried out 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 experimental data shows that RANS is capable of predicting the main features of hypersonic oblique SBLI, namely, typical size and distribution of the wall-surface pressure, and heat transfer. A large number of flow cases, at low (Re-delta 2 asymptotic to 1500) and high Reynolds number (Re-delta 2 asymptotic to 10;000), were computed to examine the scaling of the heat transfer over a wide range of wall temperatures. As expected, the interaction zone of hypersonic ramp-induced SBLI is reduced as the wall is cooled. A simple power law for heat transfer originally introduced by Back and Cuffel (AIAA Journal, Vol. 8, No. 10,1970, pp. 1871-1873) is here considered to account for hypersonic ramp-induced SBLI, which is found to successfully collapse the data to the distributions obtained for supersonic, cold/hot interactions.

Automated summary

A study was conducted on ramp-induced planar shock-wave/turbulent-boundary-layer interactions at hypersonic conditions using numerical simulation. The aim was to investigate the effects of wall temperature and Reynolds number. The results showed that the Reynolds-averaged Navier-Stokes equations could accurately predict the main features of the interactions. Various flow cases were computed to examine the scaling of heat transfer at different wall temperatures. It was found that the interaction zone decreased as the wall was cooled, and a power law originally introduced by Back and Cuffel successfully collapsed the data.