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

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

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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 envi-ronment.The results demonstrate that increasing the discharge energy is advantageous in eliminat-ing 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 con-trol 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 con-trol 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.

Hypersonic flowHigh-enthalpy flowPlasma synthetic jetShock waveFlow control

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

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College of Aerospace Science and Engineering,National University of Defense Technology,Changsha 410073,China

China Academy of Launch Vehicle Technology,Beijing 100076,China

Institute of Mechanics,Chinese Academy of Sciences,Beijing 100190,China

Institute of Mechanics,Chinese Academy of Sciences国家自然科学基金国家自然科学基金国家自然科学基金国家自然科学基金National Major Science and Technology Project of ChinaNational Major Science and Technology Project of ChinaNatural Science Program of National University of Defense Technology,China

922711101220248812072352T2221002J2019-11-0016-0037J2019-Ⅲ-0010-0054ZK22-30

2024

10.1016/j.cja.2024.01.008

中国航空学报(英文版)
中国航空学会

中国航空学报(英文版)

CSTPCDEI
影响因子：0.847
ISSN：1000-9361
年,卷(期)：2024.37(4)
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