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

• DOI: 10.1016/j.cja.2024.01.008
• Publication Date: 2024-01-11T07:34:57Z
• Authors: Xuzhen XIE; Qiang LIU; Yan ZHOU; Zhenbing LUO; Wei XIE; Guanghui BAI; Kai LUO; Qiu WANG; Jianjun WU
• Keywords: Stagnation enthalpy; Wedge (geometry); Plasma actuator

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 novel technique for reducing surface heat flux real flight environment. results demonstrate that increasing discharge energy advantageous eliminating wave, shifting wave point, and shortening control response time. oblique can be completely removed when actuator's grows from 0.4 J to 11.5 J, displacement point increases 124.56%, while time shortened 30 μs. Besides, reduction diameter exit firstly proved have negative impact on deposition working environment incoming flow, which reduces hence decreases effect. lengthens exits away second wedge. Along comparing change wall wedge over time, effect without inflation also analyzed. When works inflatable mode, both ability eliminate waves are increased significantly, reduced.