Experimental study on shock interaction control of double wedge in high-enthalpy hypersonic flow subject to plasma synthetic jet  

作　　者：Xuzhen XIE Qiang LIU Yan ZHOU Zhenbing LUO Wei XIE Guanghui BAI Kai LUO Qiu WANG Jianjun WU 

机构地区：[1]College of Aerospace Science and Engineering,National University of Defense Technology,Changsha 410073,China [2]China Academy of Launch Vehicle Technology,Beijing 100076,China [3]Institute of Mechanics,Chinese Academy of Sciences,Beijing 100190,China

出　　处：《Chinese Journal of Aeronautics》2024年第4期151-165,共15页中国航空学报（英文版）

基　　金：supported by the National Natural Science Foundation of China (Nos. 92271110, 12202488, 12072352 and T2221002);the National Major Science and Technology Project of China (Nos. J2019-II-0016-0037 and J2019-Ⅲ-0010-0054);the Natural Science Program of National University of Defense Technology, China (No. ZK22-30)。

摘　　要：The hypersonic shock-shock interaction flow field at double-wedge geometries controlled by plasma synthetic jet actuator is experimentally studied in a Ma = 8 high-enthalpy shock tunnel with the purpose of exploring a novel technique for reducing surface heat flux in a real flight environment. The results demonstrate that increasing the discharge energy is advantageous in eliminating the shock wave, shifting the shock wave interaction point, and shortening the control response time. The oblique shock wave can be completely removed when the actuator's discharge energy grows from 0.4 J to 11.5 J, and the displacement of the shock wave interaction point increases by 124.56%, while the controlled response time is shortened by 30 μs. Besides, the reduction in diameter of the jet exit is firstly proved to have a negative impact on energy deposition in a working environment with incoming flow, which reduces the discharge energy and hence decreases the control effect. The shock wave control response time lengthens when the jet exits away from the second wedge. Along with comparing the change in wall heat flux at the second wedge over time, the control effect of plasma synthetic jet actuator with and without inflation is also analyzed. When plasma synthetic jet works in inflatable mode, both the ability to eliminate shock waves and the shifting effect of the shock wave interaction point are increased significantly, and the wall heat flux is also reduced.

关 键 词：Hypersonic flow High-enthalpy flow Plasma synthetic jet Shock wave Flow control 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]