Experiments of supersonic flow and transverse injection of heated China No.3 aviation kerosene were conducted in this work. A supersonic injector was designed to gain a supersonic flowfield, in which the flow process and physical property were investigated. The physical property was calculated by the aid of SUPERTRAPP software by adopting 3-components surrogate model and compared with the experimental data. The transverse injection process of heated kerosene injected into a supersonic crossflow was investigated in a Mach 4 model combustor at various fuel temperatures and injector schemes by using high speed camera and pulsed laser schlieren system. It is found that the penetration height of heated kerosene is smaller than that of ethylene; the penetration height of injection angle of 30 degree is smaller than that of injection angle of 90 degree; supersonic injection can increase the dynamic pressure of injector exit, which results in penetration depth increased.
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