Shock Wave Oscillation at Cylindrical Cavity on Wedge Surface in Mach-7 Hypersonic Flow.

This study explores the shock wave oscillation observed near a cylindrical cavity placed on the surface of a wedge model at a 30-degree angle in Mach-7 hypersonic flow. Since the behavior of such a shock wave is key to understanding the aerodynamic heating on space vehicles, a wind tunnel test was carried out to clarify this shock oscillation problem. Flow stagnation pressure and temperature were set to 950kPa and 500K respectively. A high-speed schlieren video showed that, with a 1-cm diameter cavity, the main oscillation frequency was around 5.4 kHz. Further measurements were done to quantify this phenomenon and these detailed results will be reported in a DFD 2020 presentation.