Active control of flow-induced cavity noise using plasma actuator

Experimental study of high-frequency surface barrier discharge plasma actuators effect on flow-induced cavity tonal noise has been carried out. The tonal noise reduction in far field is demonstrated using two approaches: the excitation of artificial waves corresponding to high-frequency modes, and the stabilization of the flow using a plasma actuator in the feedback loop. It is shown that the stabilizing feedback loop makes it possible to significantly (by 10 dB) suppress the basic tone without the excitation of higher frequency oscillations. It is shown that this plasma actuators are able to reduce the flow cavity noise within the range of velocities (up to 60 m/s) typical for aircraft landing approach.