Experimental study on shock wave control in high-enthalpy hypersonic flow by using SparkJet actuator

SparkJet (SPJ) actuator was used to control shock and shock-on-shock interaction in high-enthalpy hypersonic flow with a total temperature of 4490 K Mach number 6.9 for the first time. Aiming at characteristics rarefied gas flight environment, authority SPJ improved by air supply method. The process interacting crossflow near ramp obtained using high-speed schlieren camera. When pressurized cavity pressure 133 kPa, distance 22 mm angle 50, can eliminate 68.3 % whole shock. Results different experiment cases showed that, within certain range, effect on improves increase pressure, decrease angle. elimination be explained upward motion sonic line boundary layer due formation shock, thickening heating local field. Except intersection point moves upstream downstream corresponding strength changes Accordingly, high heat around decreased. properly increasing discharge energy.