Abstract: Experimental investigation of NACA 0015 airfoil stall separation suppression by plasma aerodynamic actuation is performed for the sake of improving the flow control capability of plasma aerodynamic actuation. Research on how plasma actuation voltage, actuation position, duty cycle and pulse frequency affect the flow separation suppression effect is done. It is found that when the inflow velocity is 72 m/s, plasma aerodynamic actuation can effectively suppress flow separation on the suction side of the airfoil, which causes a lift augment of 35%. The stall angle of the airfoil increases from 18° to 21°. Experimental results indicate that the threshold voltage becomes higher as the inflow velocity becomes higher and the flow separation becomes more serious. The best position of plasma aerodynamic actuation is right at the leading edge of the flow separation origin line. Power consumption can be reduced by adjusting the duty cycle for equivalent control effects. The best control effect is obtained when the Strouhal number becomes one achieved by adjusting pulse frequency.

Key words: aerospace propulsion system, plasma aerodynamic actuation, airfoil, flow separation, flow control