Control of Shock Wave - Boundary Layer Interaction Using Nanosecond Dielectric Barrier Discharge Plasma Actuators
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2016, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved. In this study, nanosecond pulse surface dielectric barrier discharge plasma actuators are used to control shock wave boundary layer interaction in Mach 2-8 supersonic air flow. An oblique shock wave is generated by a 14 degree wedge-shaped shock generator, and interacts with the boundary layer. First, characterization of the separation region without plasma actuation is conducted to understand the interaction region based on measurement 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 occurs in this configuration. Then, three types of plasma actuator are fabricated and applied to control the separation. Schlieren images are taken with several us camera speeds and the size of interaction region or location of reflected shock wave are measured to evaluate the magnitude of the interaction. It was shown that the nanosecond surface dielectric barrier discharge plasma actuators work in two different ways: the heat generation in the boundary layer, and generation of the vorticity near the surface. In the first case the shock wave - boundary layer interaction becomes stronger and the size of separation bubble increases. In the second case the vorticity production successfully suppresses the boundary layer separation due to momentum transfer from the main flow to the boundary layer. The experimental results of the three actuator configurations provide design guidelines for nanosecond pulse driven electrodes to control the shock wave - boundary layer interaction. An optimal nanosecond pulse frequency was found through an investigation of the frequency response of the flow.
