Kim H., Lim C., Lee Y.

For the development of supersonic to hypersonic transports with high flight performance, a great interest has been taken in understanding the supersonic cavity flow features and associated unsteady phenomena during last several decades. According to the previous investigations, the pressure oscillation generated in the supersonic cavity flow is considered to be a severe source doing harm to overall performance and stable operation of aerodynamic and industrial applications, and it depends on the configuration of cavity, flow Mach number and Reynolds number. The present study describes unsteady flow phenomena generated in a supersonic flow passing over a rectangular cavity and suggests a way of control of the pressure oscillation. The three-dimensional, unsteady, compressible Navier-stokes equations are numerically solved based on a fully implicit finite volume scheme and large eddy simulation. The cavity flow are simulated with and without control methods, including a triangular bump and blowing jet installed near the leading edge of the cavity. The results show that the pressure oscillation is attenuated by both control techniques, especially near the trailing edge of cavity.