Abstract
This paper focuses on the experimental study of shock wave positioning and control of the reflection pattern by a longitudinal constricted electrical discharge in M=4 supersonic airflow. A solid wedge shock wave (SW) generator was installed in test section of SBR-50 wind tunnel. The electrical discharge was arranged on the opposite wall in the form of three plasma filaments so that the SW originating from the wedge impinged the area occupied with the plasma. As a result of the SW-plasma interaction, the flowfield was significantly modified over the test section, including an upstream shift of the shock train. The details of the plasma-SW interaction, including the transitional effects, are explored with wall pressure measurements, schlieren imaging and Mie scattering visualization. The criterion of effective flow control by near-surface plasma filaments is discussed.
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