Investigation of supersonic separated flow in a compression corner by laser doppler anemometry

A single-component, computer-operated, three dimensional traversing Laser Doppler Velocimetry system was designed and constructed for a supersonic wind tunnel. The model was a 10° compression corner, providing an example of laminar boundary layer separation. Static pressure data and color schlieren photographs were taken. The Mach number was 2.42 and the Reynolds number was 2.13 x 105. The flow was seeded with submicron sized oil droplets.The trend of decreasing upstream influence with increasing Reynolds number was confirmed. Mean velocity profiles provided experimental evidence of reversed flow. Points of separation and reattachment were consistent with those determined by schlieren and pressure scans. The flow was of the laminar type until downstream of reattachment. Individual mean velocity and turbulence profiles, as well as velocity histograms are presented.