Experimental study of two-dimensional shock wave/turbulent boundary layer interactions

Abstract

For high speed air-breathing engines, knowledge of the point at which boundary layer separation occurs limits the design parameters. Shock wave/turbulent boundary layer interaction is a common occurrence in supersonic flows with almost any flow deflection accompanied by shock formation. Incident shock interactions occur when the shock that impinges on the boundary layer is generated by an external source. These allow for the study of the interaction of bulk flow compression without the added effects of streamline curvature and hence are used for this work. They are particularly important for scramjet studies which involve ducted flows where there is a requirement to add as much heat and pressure as possible. However analytical means of modeling separated flow are not advanced.