Plasma-actuated flow control test in high enthalpy shock tunnel

The use of plasma flow control to improve the aerodynamic performance of aircraft is a hot research topic in the field of flow control in recent years. In this paper，based on the high total temperature and high Mach number freestream of the detonation-driven high enthalpy shock tunnel，the influence law of surface arc discharge technology on the flow structure of the flow field and contact measurement methods，such as heat flux and pressure，are investigated. The results show that the influence of arc discharge on the double wedge flow structure can be divided into the phases of interference shock generation and recovery of the original shock，and its action time on the flow structure is about 66. 68 μs. The effect of arc discharge on the space potential causes interference with the measurement data of contact methods such as thermocouples and piezoresistive sensors. The interference time in the test state of this paper is about 200 μs，which is much longer than the action time of the discharge on the flow. Additionally，the low-pass filtering method，the noise amplitude and the weighted processing of the noise time domain amplitude can optimize the interference signal of pressure and temperature to a certain extent and obtain relatively reasonable test data. However，the processing method still needs more abundant test data for verification. © 2022 AAAS Press of Chinese Society of Aeronautics and Astronautics. All rights reserved.