Supersonic Flow Control of Swept Shock Wave/Turbulent Boundary Layer Interaction Using Plasma Actuators
Abstract
The effect of plasma actuators on the physics of the swept shock-wave/boundary-layer interaction induced by a sharp fin is investigated in this study by means of Reynolds-averaged Navier-Stokes calculations, using the SU2 code developed at Stanford University. The present work focuses on a sharp-fin configuration placed in a Mach 5 flow, with a spatially developing turbulent boundary layer, at an angle of attack of 12 deg. At the streamwise location of the fin leading edge, the Reynolds numbers based on momentum thickness and boundary layer thickness for the undisturbed boundary layer case are around 5075 and 3.321 mm, respectively. The mean pressure distribution and heat transfer data at the wall for the case without any actuators were compared to experimental data. The plasma actuator is modeled semi-empirically as a heating source and magnetic bodyforce term, which is included in the energy and momentum equations respectively. The plasma actuator is placed within the boundary layer at a certain distance upstream of the mean separation line. A horse-shoe vortex is created as the streamlines encounter the disturbance, which decays some distance downstream. The heat addition due to actuator acts as a virtual fillet, which slows the compression and makes separation more gradual. The resulting time-averaged flow fields showed decreased intensity of the reflected shock wave, reduction in peak skin friction coefficient, and increase in the separation bubble length with plasma actuator control.^
Degree
M.S.
Advisors
Jonathan Poggie, Purdue University.
Subject Area
Engineering|Aerospace engineering
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