Effects of suction on the interaction between shock wave and boundary layer at a compression corner

Abstract

The report describes work carried out in a supersonic wind tunnel at a Mach number of 1.93 on the interaction produced by wedges of 8°, 12° and 16° angle. The wedges could be raised from the tunnel floor through distances comparable with the boundary layer thickness, and suction was applied at the resulting slot. The pressure distributions and boundary layer traverses show how the suction reduces and eventually eliminates the separation region, causing the flow to approach that of ideal fluid theory. Estimates of optimum suction quantity and bleed height are obtained.