Flow Control of a Sharp-Edged Airfoil

An experimental study of active control of fully separated flow over a symmetrical circular-arc airfoil at high angles of attack was performed. The experiments were carried out in a low-speed, open-circuit wind tunnel with the airfoil at angles of attack from 10 to 40 deg. Low-power input, unsteady excitation was applied to the leading or trailing edge. The actuation was provided by the periodic oscillation of a 4% chord flap placed on the suction side of the airfoil and facing the sharp edge