In recent year, research and development activities for next generation supersonic transport are being car-ried out actively by the world aeronautical community. In a supersonic intake, a cavity plays an important role in the control of shock waves. The study of the supersonic internal flow with the cavity is important not only for resarch on industrial applications but also for basic research in gasdynamics. In the present study, the supersonic internal flow with cavities was investigated experimentally by a schlieren optical method and pressure measurements in the case of the flow Mach number 1.9 at the cavity entrance. The effects of configurations of cavity leading edge and porous wall on the flow-induced pressure oscillation were clarified qualitatively.