Control effect of arc-driven plasma synthetic jet on supersonic shockwave

Experimental investigation of supersonic shockwave controlled by arc-driven plasma synthetic jet (PSJ) is presented. A typical single orifice plasma jet actuator, with cylindrical cavity of 4mm deep and diameter of 4mm, is adopted, in which arc discharge is triggered by a pulsed DC power supply. High temperature and pressure air is then generated and injects into the main flow. In Mach 2.5supersonic flow, the control effect of shockwave induced by a 15° compression corner is clearly observed. The angle of oblique shockwave is reduced from 35° to 31°，whilethe position of shock foot moves upstream by 1.8mm. Due to the pulse frequency limit ofpower supply, the control effect cannot be sustained. For stronger and more stablecontrol ability, as well as further understanding on the relationship between actuation design and control result, the modeling based onexperiment is fulfilled. Through numerical simulation, the influence of some key parameters,such as power density of discharge, the location of jet orifice,and number of actuator, is discussed. Results show that more energy deposition brings more obvious shockwave variation. However, the control effect is weakened with longer distance between jet orifice and start of compression corner. Two actuators triggered simultaneously can improve the control effect without the increase of pulse frequency, while two actuators workalternatively hardly provide better control effect.