The effect of plasma actuators on a swept shock-wave/boundary-layer interaction induced by a sharp fin was investigated by means of Reynolds-averaged Navier–Stokes calculations. The work focused on a sharp-fin configuration in a Mach 5 flow, at an angle of attack of 12 deg, and with a momentum thickness Reynolds number of about 5100. The mean wall pressure and heat transfer predicted for the baseline flow were compared to experimental data. The plasma actuator was modeled semi-empirically with a heat source and a magnetic body force imposed in the boundary layer upstream of the mean separation line. A horseshoe vortex appeared with the presence of the model actuator and decayed some distance downstream. The flow heating by the actuator acted as a virtual fillet, which slowed the compression and made separation more gradual. Decreased intensity of the separation shock wave, reduced skin friction coefficient, and increased separation bubble size were observed with the application of control.
Flow Control of Swept Shock-Wave/Boundary-Layer Interaction Using Plasma Actuators
Journal of Spacecraft and Rockets ; 55 , 5 ; 1198-1207
2018-06-27
10 pages
Article (Journal)
Electronic Resource
English
NUMERICAL INVESTIGATION OF SHOCK-WAVE/BOUNDARY-LAYER INTERACTION CONTROL USING PLASMA ACTUATORS
British Library Conference Proceedings | 2011
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