Abstract: Based on surface arc plasma aerodynamic actuation, demonstration experiments have been conducted on the variation rules of the shock wave’s position, degree and intensity through varying actuation conditions (such as discharge channel number and spacing, DC discharge voltage, ramp angle and magnetic field) in Mach number 2.2 supersonic flow. The results indicate that, when applying plasma aerodynamic actuation, the start position of the shock wave moves upstream 1 mm to 8 mm averagely, the shock wave angle decreases by 4% to 8% averagely, and the shock wave intensity weakens by 8% to 26% averagely. The local plasma aerodynamic actuation can produce high temperature and pressure plasma layer. The plasma layer makes the separation point of the boundary layer move upstream, which changes the