Lift Enhancement by Plasma Actuators at Low Reynolds Numbers

Abstract

This paper describes an experimental investigation into the use of trailing-edge-mounted plasma actuators for lift enhancement at low Reynolds numbers. The measurements were performed using a 0.2 m chord NACA 0009 airfoil with a plasma actuator mounted at , and over the Reynolds-number range . Force-balance data are presented that show that the effect of the actuator varies significantly with wind speed and angle of attack, and that, at some test conditions, the actuator produces a reduction in the airfoil lift. Detailed surface-pressure and Laser-Doppler-Velocimetry measurements show that the precise actuator effect depends upon how the actuator flowfield interacts with the trailing-edge boundary layer at the particular conditions of the test, and that the observed variation in actuator effect is a consequence of the different trailing-edge boundary-layer flows that can occur at low Reynolds numbers.