Kussoy et al[1] performed extensive experimental measurements on a Mach 8.3 flow in a wedge inlet configuration. To predict this complex 3D flowfield, involving crossing shock/boundary layer interactions, CFD++ was used on a mesh consisting of approximately 250,000 cells. Centroidal locations adjacent to walls were at y+ of approximately 60 and a wall function which accounts for compressibility and heat transfer effects was employed. The single equation R model was employed. The figures below show the topology, an overview of the flow in the region of the wedges, showing pressure contours on one wedge surface and streamlines, and comparisons of predicted wall pressure and heat transfer, along the symmetry line, with corresponding measurements. Excellent agreement is obtained.

[1] Kussoy, M.I., Horstman, K.C. and Horstman, C.C., `Hypersonic Crossing Shock-Wave/Turbulent-Boundary-Layer Interactions', AIAA J. Vol. 31, 1993, pp. 2197-2203.