Suppression of Wingtip Vortices Using Plasma Flow Control
Semester of Graduation
First Major Professor
Dr. Hui Hu
Master of Engineering (MEngr)
An attempt to use Alternating Current Dielectric-Barrier-Discharge actuators to suppress wingtip vortex of a finite wing. A NACA 0012 wing with AC-DBD actuators embedded at the wingtip was used at a Reynolds number of approximately 150,000. A stereoscopic PIV system measured the wake at multiple distances behind the trailing edge. A JR3 multi-axis load cell was used to simultaneously measure the forces on the wing. The angle between the AC-DBD actuators and U∞ changed to determine any impact on the wingtip vortex. Repeated efforts lead to the conclusion that the AC-DBD actuators were too weak to have an observable effect on the wake vortex.
Harper, Eric, "Suppression of Wingtip Vortices Using Plasma Flow Control" (2019). Creative Components. 315.