In order to investigate the supersonic combustion characteristics, the model scramjet engine was tested with T4 free piston shock tunnel at University of Queensland. The free stream test condition was fixed at Mach 7.6 at an altitude of 31 km. For this experimental study, the effects of varying the fuel equivalence ratio and the influence of the cavity and the shape of cowl were investigated. Numerical analysis was also performed to understand the flow and combustion characteristics. As a result, supersonic combustion was observed at equivalence ratios between 0.11 and 0.18. Measurements indicated that the engine thermally choked at a fuel equivalence ratio of 0.40. Furthermore, cavity flame holder and W-cowl showed reaction enhancing effects.
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