Abstract
In this study the combustion process in a SHCRAMJET using cantilevered compression and expansion type ramp injector having 80 of both compression and expansion angle is analyzed using FLUENT software. After designing the model in GAMBIT, it is exported to FLEUNT software for analysis of combustion process with air inlet at Mach number 7 and hydrogen as the fuel with inlet Mach number 3.5. The results obtained explain the significance of geometries of the injector in initiating combustion process and achieving enhanced air-fuel mixing. The contours of temperature, pressure, density, turbulent intensity and mass fraction of H2O formed explain the extent of combustion taking place in this case.
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