Study of Plasma-Based Vortex Generator in Supersonic Turbulent Boundary Layer

The problem of flow control under conditions a turbulent boundary layer at transonic and supersonic free-stream velocities is considered. Such flows are integral components the flight process exert significant effects on around both aerodynamic object as whole its individual elements. present paper describes investigations combined device (“plasma wedge”), which wedge mounted along with energy supply one side owing to spark discharge. strategy by this based increasing momentum in layer, enhances resistance adverse pressure gradient and, consequence, separation further downstream. study includes experimental computational aspects. examined evolves rectangular flat plate sharp leading edge Mach number M = 1.45 unit Reynolds numbers Re1 11.5·106 1/m. experiments performed velocity fields distribution wake behind actuator. results show that streamwise vortex formed actuator when discharge initiated. Reasonable agreement data numerical simulations allows conclude Reynolds-averaged Navier–Stokes equations suitable tools for solving