This case is a two-dimensional Mach 9 flow over a 38 deg. cooled ramp, with experimental data measured by Coleman and Stollery[1]. An oblique shock, impinging on the boundary-layer downstream of the ramp corner, induces flow detachment with subsequent reattachment onto the ramp surface where a large heat-transfer peak occurs. The first figure below shows the geometry and main flow features. Traditional turbulence models - even nonlinear closures - grossly overpredict the heat-transfer levels. CFD++ has several approaches to overcome this problem. The results below are by a dual-dissipation k-e model - the k-e-R closure[2]. While the pressure is predicted well by both models, the heat-transfer is vastly overpredicted by the cubic closure but not by the k-e-R model.

[1] Coleman, G.T. and Stollery, J.L., `Heat-Transfer from Hypersonic Turbulent Flow at a Wedge Compression Corner', J. Fluid Mech. Vol. 56, Pt. IV, 1972, p. 741.
[2] Goldberg, U. and Batten, P., `Heat-Transfer Predictions using a Dual-Dissipation k-e Turbulence Closure', submitted to AIAA J. Thermophys. & Heat-Transfer. Also to be presented in the AIAA 39th Aerospace Sciences Meeting, Reno, NV, Jan. 2001.