LAUSR

The problems of the control of steady three-dimensional viscous incompressible flows modeling the gas flow in the vicinity of the attachment line on the leading edge of a swept wing are considered. It is assumed that the control is realized by means of the body force action approximating the action of a periodic sequence of plasma actuators mounted perpendicular to the leading edge. The corresponding boundary value problems for the system of Navier–Stokes equations are numerically solved using the Fourier method along the longitudinal coordinate and second-order difference approximation in the vertical coordinate. An important role played by the control-induced pressure gradient is shown.