Mixing and combustion characteristics of several fuels in supersonic air streams are investigated numerically. Four case studies with three different configurations are used. All of them feature the existence of a generic rearward-facing step in one of the longitudinal walls. The effect of pilot hydrogen injection on the combustion of hydrogen, ethylene and kerosene fuels injected normal to the incoming supersonic air stream is investigated. The results for the transverse sonic hydrogen injection and the vertical single-hole sonic hydrogen with hydrogen pilot injection show the typical features of such flowfields. The existence of a wedge downstream of the rearward-facing step showed a good potential towards enhancing the fuel-air mixing in addition to helping initiating and stabilizing the main flame. The current work is still underway to complete studying the combustion flowfield of liquid kerosene injection with pilot hydrogen as a comprehensive study to address the possibility of using hydrocarbon fuels in the mid-speed range of the hypersonic flight.
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