Structure and stability of a supersonic boundary layer with a transverse pressure graduent induced by an oblique shock waves
A.A. Sidorenko, S.V. Kirilovskiy, T.V. Poplavskaya
Khristianovich Institute of Theoretical and Applied Mechanics SB RAS, Novosibirsk, Russia
Keywords: shock wave interaction with the laminar boundary layer, boundary layer stability, numerical simulation
Abstract
Results of numerical simulatgions 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 еN-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 develop-ment of Tollmien-Schlichting instability waves and crossflow instability.
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