Title
Suppression of Wingtip Vortices Using Plasma Flow Control
Degree Type
Creative Component
Semester of Graduation
Summer 2019
Department
Aerospace Engineering
First Major Professor
Dr. Hui Hu
Degree(s)
Master of Engineering (MEngr)
Major(s)
Aerospace Engineering
Abstract
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.
Copyright Owner
Harper, Eric
Copyright Year
2019
File Format
PP
Recommended Citation
Harper, Eric, "Suppression of Wingtip Vortices Using Plasma Flow Control" (2019). Creative Components. 315.
https://lib.dr.iastate.edu/creativecomponents/315
