The standard k- ε turbulence model, two dimensional NavierStokes equations along with eddy-dissipation/finite-rate reaction model has been applied to analyze the flow dynamics of the scramjet combustor with the cold-flow and ignited engine conditions. In the present work, all the simulations have been carried out by using ANSYS Fluent code. Simultaneously, the validation of the present work is completed by comparing its result with available experimental data which is available in the literature. It is observed that the computational results are in good qualitative agreement with the experimental data. The significance of injection temperature, pressure and the movement of the shock-wave train are analyzed using simulations. It was inferred that the mode transition could be achieved through increasing the injection pressure and decreasing the injection temperature. However, at higher injection pressure, the shock-wave train got shifted towards the outer periphery of the isolator resulting in inlet-flow un-start. Compared to injection pressure, injection temperature exhibited lower significance over mode transition. Keywords: Scramjet, CFD, Combustor, Hydrogen, Injection pressure and temperature
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