Oscillating Shock Impingement on Low-Angle Gas Injection into a Supersonic Flow

摘要

Experiments were performed to determine effects of impinging oscillating shocksof different frequencies on a 15 deg downstream angled, underexpanded, sonic helium jet injected into a supersonic airflow. Information on mixing, penetration, total pressure loss and turbulence structure from these experiments was used to estimate mixing control achieved by adding an oscillating shock to the helium injection flow field. Tests were conducted at Mach 3.0, with a total pressure of 6.5 atm, total temperature of 290 K and a Reynolds number of 51.0 million/m. Oscillating shocks of 3 different frequencies were studied. Frequencies selected were designed to allow tuning of the shock frequency to the