Flow diagnostics in shock wave-boundary layer interaction experiments in hypersonic flow

Shock Wave-Boundary Layer Interaction (SBLI) is a phenomenon occurring in highspeed propulsion systems that is highly undesirable. Numerous methods have been tested to manipulate and control SBLI which includes both active and passive flow control techniques. To determine the improvements brought by the flow control techniques, advanced and state-of the-art flow diagnostics and experimental techniques are required, especially when it involves high-speed flows. In this study, a number of advanced flow diagnostics were employed to investigate the effect of micro-vortex generators in controlling SBLI in Mach 5 such as Pressure Sensitive Paints (PSP), Particle Image Velocimetry (PIV), schlieren photography and oil-flow visualization. The flow diagnostics provided both qualitative and quantitative information of the boundary-layer separation. The improvements of the separation region controlled by the micro-vortex generators were clearly visualized and characterized