Dynamic Stall Control by NS SDBD Actuator
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© 2018, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved. In the last two decades, nonequilibrium plasmas have demonstrated the ability to affect a variety of flows of aeronautical interest, including mitigation of stall on steady airfoils. Plasma actuation shows promise to address dynamic stall in rotorcraft as it is a nonintrusive, active control method. In this study, nanosecond pulsed Surface Dielectric Barrier Discharge (ns-SDBD) plasma devices are used to control boundary layer separation on a pitching airfoil. Actuators operate in continuous mode in the range of 50-500 Hz with 20kV, 25ns FWHM pulses. For a Reynolds number of 4.5×105 and reduced frequency of 0.02, stall mitigation is demonstrated for angles of attack up to 32 degrees and increase in lift of up to 20%. The common issue of Retreating Blade Stall (RBS), as experienced in helicopters, was also considered in this study by experimenting with a reverse flow over an airfoil. Increases in lift are demonstrated for separated flows with Reynolds numbers up to 7×105 and reduced frequencies k ≤ 0.05, with angles of attack up to 32 degrees. Increases in lift with plasma control are demonstrated to be up to 55% for reversed flow. Changes in drag with plasma actuation for all tests are within 10% in the stall regime.
author list (cited authors)
Starikovskiy, A., Meehan, K., & Miles, R. B.