Plasma flow control of the tip vortices over a very low aspect-ratio wing

Abstract

Flow control of the tip vortices over a very low aspect-ratio wing was carried out using the dielectric-barrier-discharge plasma actuators. The results indicate a large change in the aerodynamic forces by plasma flow control, where the lift coefficient is increased by the blowing plasma actuator by 23% and is reduced by the suction plasma actuator by 30%. The change in the drag coefficient is less than 10%. The blowing plasma moves the tip vortex outboard away from the wing tip, increasing the streamwise vorticity as well as the turbulence intensities and the Reynolds stress. With the suction plasma, the tip vortex is shifted inboard closer to the wing tip. Co-flowing with the tip vortex, the blowing plasma increases the tip vortex circulation, while it is reduced by the counter-flowing suction plasma.