Control of turbulent boundary layer by plasma-based actuator

Abstract

The problem of flow control under conditions of a turbulent boundary layer at transonic and supersonic free-stream velocities is considered. Such flows are integral components of the flight process and exert significant effects aircrafts characteristics. In the paper investigations of a combined control device (“plasma-wedge”), which is a wedge (fin) mounted lengthwise the flow with energy supply at one side of the wedge by exciting a spark discharge. The investigations was carried out on rectangular flat plate with sharp leading edge, at zero angel of attack, freestream Mach number M=1.46 and singles Reynolds number Re1=11.5 106·1/m. The results show that a streamwise vortex is formed in the wake behind the actuator when the discharge is initiated. Reasonable agreement of the experimental data with numerical simulations allows one to conclude that the Reynolds-averaged Navier-Stokes equations are suitable tools for solving the problem considered.