Contour design and numerical calculation of certain solid propellant rocket motor nozzle

According to the entire design requirements and restraints of a certain solid propellant rocket motor,design method of nozzle contour is put forward. In this method,muzzle internal flow field,pressure against nozzle wall and temperature variation under different pressures are analyzed by applying Computational Fluid Dynamics(CFD),one-equation model: S-A Turbulent Model and finite volume method.According the results of computation of flow field,instantaneous propulsion of motor is gained,which is compared to the result of ground test.