Wing Circulation Control using a Dielectric Barrier Discharge (DBD) plasma actuator. A surface plasma actuator was placed on the suction surface near the trailing edge of an airfoil to enable Coanda effect that changes the flow circulation. Wind tunnel experimental results and PIV results show that the method is able to provide lift enhancement and drag reduction on a single element wing.

Low speed flow around an airfoil was controlled by a surface dielectric barrier discharge (DBD) plasma actuator placed on the suction surface near the trailing edge of the airfoil. The plasma actuator was used in place of tangential jet blowing for circulation control. A wall jet was induced near the trailing edge which produced Coanda effect and altered the overall circulation around the airfoil. The circulation and lift of the airfoil were changed directly by the plasma actuation. The effectiveness of plasma circulation control of the airfoil was investigated using particle image velocimetry and surface pressure taps. Results suggested that the plasma actuation produced lift enhancement.