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

File Format

PP

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