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