To calculate the flow filed in a rocket motor under the condition of different rotate speed, the RNG k-ε turbulent model was adopted to calculate the 3D flow filed in a rocket motor with inner-burning tube solid propellant. The user defined function (UDF) was adopted to describe the condition of mass flow inlet. The calculation results show that the flow field in combustion chamber and nozzle of high-speed spinning SRM is complex. The tangential velocity distribution of the flow closed by front blockage in the chamber is similar to Rankine combination swirl, and in nozzle it is similar to the forced vortex. The tangential velocity reached two extremums in combustion chamber and the throat of nozzle. The tangential velocity changed rapidly, and reached two extremum, the negative value of axial velocity appeared near axis. High-speed spinning has a serious effect on the structural strength and thermal protection of the former head of combustion chamber and nozzle thoart.
