- 1 PartF
© 2020, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved. In this study, a quasi direct-current (Q-DC) filamentary plasma was employed for control of Mach-4 supersonic flow over a compression ramp. A 15-degree ramp model was placed on a test section wall at the SBR-50 facility. An array of 5 electrodes were installed 30 mm upstream of the ramp to attain rapid flow control. Schlieren visualization was performed with a high-speed camera to clarify the details and dynamics of plasma-flow interaction. Kulite™ pressure transducers were placed over the test model to measure the fast pressure disturbances. The data on pressure dynamics at the ramp was analyzed to evaluate the plasma actuation effectiveness. The flowfield structure and shock wave positions were significantly modified due to the Q-DC plasma actuation. The pressure on the ramp was reduced during the plasma pulse and the reduction was nearly a linear function of plasma power. It was also found that the pitching moment coefficient around the leading edge of the ramp is a linear function of a relative plasma power, suggesting a linear control of aerodynamic moments at practical application.