Abstract
This study is concerned with the flow control around airfoil when a dielectric barrier discharge(DBD) plasma actuator is mounted on the leading edge. Lift force and velocity field around the airfoil are measured for the on and off modes of the plasma(pulse modulated drive). As a result, the behavior of the variation in the lift force is different depending on the modulation frequency. Over the angle of maximum lift, there is the most effective driving time period to avoid decreasing the lift force, and the strong vortex structure are formed in the shear layer.
