Plasma control of a turbulent shock boundary-layer interaction

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[1] [1,Bisek, Nicholas J.
[2] 1,Rizzetta, Donald P.
[3] 1,Poggie, Jonathan
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| 1789年 / AIAA International卷 / 51期
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The Navier-Stokes equations were solved using a high-fidelity time-implicit numerical scheme and an implicit large-eddy simulation approach to investigate plasma-based flow control for supersonic flow over a compression ramp. The configuration included a flat-plate region to develop an equilibrium turbulent boundary layer at Mach 2.25; which was validated against a set of experimental measurements. The fully turbulent boundary-layer flow traveled over a 24 deg ramp and produced an unsteady shock-induced separation. A control strategy to suppress the separation through a magnetically-driven surface-discharge actuator was explored. The size; strength; and placement of the model actuator were based on recent experiments at the Princeton University Applied Physics Group. Three control scenarios were examined: steady control; pulsing with a 50% duty cycle; and a case with significant Joule heating. The control mechanism was very effective at reducing the time-mean separation length for all three cases. The steady control case was the most effective; with a reduction in the separation length of more than 75%. The controller was also found to significantly reduce the low-frequency content of the turbulent kinetic energy spectra within the separated region and reduce the total turbulent kinetic energy downstream of reattachment. Copyright © 2013 by the American Institute of Aeronautics and Astronautics; Inc;
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