Planar Shock Wave Interactions on Turbulent Boundary Layer over Cylindrical Body

Stereoscopic particle image velocimetry and high-speed pressure sensitive paint measurements were performed for supersonic impinging shock-wave/turbulent-boundary-layer interactions over a cylindrical surface, at Mach 2.7. A turbulent boundary layer develops naturally along a half-cylindrical body, aligned axially with the flow; the shock-wave interaction with this boundary layer is then studied along the windward plane of symmetry of the half cylinder. This study investigates the influence of shock angle and shock generator mounting height. Both weak and strong interactions are identified within the data, which differ according to size of the the interaction region and the presence of appreciable reverse flow. The flowfield is highly sensitive to the relative position of the shock generator with respect to the surface, which manifests in quantifiable differences in turbulence kinetic energy across the test matrix.