Upstream disturbances on compressible convex corner flows

An experimental program was conducted to investigate the upstream blowing rate and air injection pattern on compressible convex corner flows. This upstream disturbance tends to decrease the local Mach number, adverse pressure gradient downstream of the corner and peak pressure fluctuations in subsonic interactions. This results in the delay in transition of subsonic and transonic expansion flows. Upstream movement of shock wave in transonic interactions is coupled with the enhanced shock oscillation and higher level of downstream surface pressure fluctuations. The effect of air injection pattern is more pronounced on the intensity of peak pressure fluctuations.