Structure and stability of a supersonic boundary layer with a transverse pressure gradient induced by an oblique shock waves

Results of numerical simulations of interaction of a supersonic boundary layer on a flat plate with an oblique shock wave generated by a thin wedge aligned at a right angle to the plate surface are reported. The problem is solved by means of combining a CFD code based on solving the Reynolds-averaged Navier–Stokes equations with the LOTRAN 3.0 software package based on the eN-method. Specific features of the flow structure with primary and secondary separation regions are identified. It is shown that the shock-induced pressure gradient leads to the development of Tollmien-Schlichting instability waves and crossflow vortex instability.