Abstract: The characteristics of hydrogen transverse jet supersonic combustion flow field of scramjet under different inlet conditions were numerically simulated and analyzed. Numerical simulation technology is the main method to study the fuel combustion and flow field structure of wide range scramjet, due to the limitation of experimental technology and equipment. Based on the hybrid mesh, the finite volume method for multi-component N-S equations solver was used to simulate the flow of hydrogen transverse jet combustion in the supersonic combustor with wedge/cavity structure, with different Mach numbers and pressures of inlet. The penetration depth of the hydrogen jet, the structure of separation around jet, the mixing efficiency and the combustion efficiency were discussed to show the change of flow field. The results can offer some references for the analysis of the jet combustion flow field in a wide range scramjet.