Experimental study of the possibility of using acoustics to control flow separation on the wing of an aircraft.

Аuthors

Gorev . N., Popov S. A.^*, Kozlov V. V.

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*e-mail: flowmech@mail.ru

Abstract

Experimental studies of flow patterns of the wings in the subsonic wind tunnel for a wide range of angles of attack, even before the flow separation. The possibility of control of flow separation by means of a localized vibrating element. In the experiment, we used the method of weight measurements and measurements of the pressure distribution through the drainage holes on the surface of the model. It is shown that, in the arrangement of small-size aircraft can be placed transmitters on the surface of the wing - a membrane embedded in the surface and can be placed in the fuselage emitters irradiating wing.

Keywords:

wind tunnels ofMAI, the model wings, flow separation, the sound emitter;

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