Control of Shock-Wave/Boundary-Layer Interaction Using Nanosecond-Pulsed Plasma Actuators
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Copyright 2017 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved. Nanosecond-pulsed surface dielectric barrier discharge plasma actuators are used to control shock-wave/ boundary-layer interactions. Characterization of the separation region without plasma actuation is conducted to understand the interaction based on measurements of pressure distribution, schlieren imaging, and velocimetry by the femtosecond laser electronic excitation tagging technique. The results show a weak separation due to the interaction. Three types of plasma actuators are applied to control the separation. Schlieren images are taken by a high-speed camera to evaluate the magnitude of the interaction. It is shown that the plasma actuators affect the flow in two different ways: heat generation in the boundary layer, and generation of vorticity near the surface.When the first effect is dominant, the shock-wave/boundary-layer interaction becomes stronger and the size of the separation bubble increases. If the vorticity generation prevails, it suppresses the separation due to the momentum transfer from the main flow to the boundary layer. The experimental results of the three actuator's geometries provide the design guidelines for nanosecond-pulse-driven electrodes to control the interaction.An optimal actuation frequency is found through an investigation of the frequency response of the flow.
