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In the present paper, a Nano-second pulse actuator is applied to a NACA0012 airfoil in the condition of Re = 63,000 (U∞=10m/s) and leading edge separation control capability of a Nano-second pulse actuator is investigated. Angle of attack is changed in pre-stall angle, post-stall angle and deep-stall angle. At pre-stall angle, nano-second pulse actuation can move the reattachment point to upstream direction and shorten the separation bubble. This suggests that the nano-second pulse actuation can enhance turbulent transition of shear layer. At post-stall angle and deep-stall angle, higher peak voltage is more effective for separation control, though actuation of x/c=0.1 at the deep-stall angle has no capability for separation control at any peak voltage. Comparing the controlled cases at post-stall angle and deep-stall angle, the appropriate repetition frequency is different between the cases.

G0406 Experimental Study of Nano-second Pulse Plasma Actuator for Low Reynolds Number Separated Flow Control