Abstract
The process of flow control in the swept-wing boundary layer using a number of plasma actuators mounted at an angle to the leading edge is theoretically studied. The resonance response of the controlled flow is investigated when the angle of inclination of the actuators is close to the angle of inclination of the stationary vortices of cross-flow instability. The calculation of the controlled flow is carried out within the framework of the parabolic system of Navier–Stokes equations. The stability characteristics of periodic flows formed by the action of a control bulk force are calculated.
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