摘要: This paper updates the experimental results obtained at serial work focused on shock wave train control in duct-driven supersonic flow (see AIAA Papers 2023-1864, 2022-2533). After the previous tests, an important question remains... 展开 This paper updates the experimental results obtained at serial work focused on shock wave train control in duct-driven supersonic flow (see AIAA Papers 2023-1864, 2022-2533). After the previous tests, an important question remains open on what is a limit of the plasma control effect in terms of impinging SW position vs plasma. In this work, a significantly elongated constricted electrical discharge in M=2 supersonic airflow was applied. A fixed solid wedge shock wave (SW) generator was installed on the top wall of test section of Notre Dame's SBR-50 wind tunnel. The electrical discharge was generated on the bottom wall such that the compression SW impinged near the end of three plasma filaments. By replacing the conductive metal wall with flush mounted grounding rails embedded in an insulating ceramic, the electrical discharge is highly elongated to distances up to around 130 mm. While details of the plasma-SW interaction have been elucidated in previous work, the results presented here demonstrate that control of the shock train via upstream pressure drain through the zone of heating is equally viable at significantly longer distances. While power demands for longer filaments are slightly increased, the increased control authority can lead to a much greater modification of the entire shock train. 收起