Wind tunnel experimental investigation on wing stall separation suppression was performed and the influence of pulse frequency

voltage

duty cycle and actuation position on flow control effect was analyzed. The results showed that

at the free-stream velocity of 35m/s

the flow separation on the suction side of the wing under large angle of attack was suppressed effectively and the critical stall angle of attack increased from 17° to 19°. The maximum lift coefficient increased by 9.45% with a drag reduction of 20.9%. Experimental results demonstrate that control effect is best when frequency is 200Hz and the corresponding dimensionless actuation frequency is 1. Larger voltage is needed with the increase of the angle of attack because the 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 decreasing the duty cycle at the same control effect.