Abstract
In recent years, research and development activities for next generation supersonic transport are being carried out actively by the world aeronautical communities. In a supersonic air-intake, a cavity with bleed plays an important role in the control of normal shock wave under the cavity/shock wave interaction. The supersonic air-intake flow tends to be unstable due to the shock wave/wall boundary layer or the shock wave/shear layer interactions occurring close to the leading edge of the cavity. In the present study, the effects of cavity/shock waves interaction on the pressure oscillation in the cavity were investigated experimentally in the case of the flow Mach number 1.75 at the cavity entrance and the characteristics of oscillation in the cavity were analyzed using the wavelet transforms.
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