Abstract
Experimental investigation controlling a trailing edge separation on a wing in ground effect is carried out. The Dielectric Barrier Discharge (DBD) plasma actuator with pulse modulated driving is used for the control. As a result, the trailing edge separation is suppressed by means of the plasma actuator, so that the drag coefficient is decreased and lift-drag ratio is increased. The lift-drag ratio becomes maximum when the actuator is located at 75% chord from the leading edge.
