Experimental Investigation of the Active Flow Control over a Cranked-Delta Wing

What is it about?

The effects of pulsed DBD plasma actuator on the surface pressure distribution of a cranked-delta wing model at various angles of attack and at subsonic speed have been investigated. The data are compared with the cases without DBD actuators. It is seen that DBD can improve the surface pressure distribution at high angles of attack, beyond static stall angles.

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