© 2019, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved. This study examined the control effect of Q-DC electric discharge on the surface pressure of a 12-degree compression ramp in Mach-2 supersonic flow. The experiments were conducted in the supersonic wind tunnel SBR-50 at the University of Notre Dame. Stagnation pressure and temperature were varied as P0=1-3bar and T0=300-600K respectively to attain various flow conditions. Ramp pressure measurements, schlieren visualization, and high-speed camera imaging were used for evaluation of plasma control effects. Plasma voltage spectra based on FFT analysis indicated that there are multiple characteristic frequencies, which are correlated with repetitive plasma motion through dynamic mode decomposition analysis and categorized into streamwise-and transverse-oscillation modes. Ramp pressure variation was found to be a linear increasing function of average plasma power and plasma power to flow enthalpy flux ratio.
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