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For the problem of interaction between rocket gas jet and supersonic inflow, this paper has investigated the relevant flow field characteristics by numerical simulation. Firstly, a computational program was developed using high-resolution schemes to solve complex supersonic flow field, which solves the Navier-Stokes equations based on a multi-block structural grid using finite volume method as well as k − ω SST turbulence model. Then, a classical experiment was conducted to validate the developed code. Results show that the rocket jet strongly interacts with the supersonic inflow that results in complex wave structure. The nozzle inlet mass flow rate has an important influence on the interaction. When the mass flow rate is in a low level, flow separation and shock train occur in the divergent region, leading to violent oscillation of flow. With the mass flow rate of nozzle inlet increasing, the rocket gas expands continuously after passing the nozzle outlet and the rocket jet would induce more complex shocks.