关键词: 固体火箭发动机;尾喷管;轴对称流;流场

Abstract: The study in this paper is a part of the research work about flow field in a central dump combuster for solving the problem of nozzle throat sedimentation. According to the k-ε kinetic turbulent model and the condition of constant viscosity,the flow fields under three different kinds of velocity distributions are computed.The results,compared with the experimental data obtained from home and abroad and the computational results by spalding, are very satisfactory. At the same time, some attention has been given to the change of flow field under moving boundary conditions in order to predict the effect of sudden expansion flow theoretically.The SIMPLE method has been used to solve the flow field discribed by a set of nonlinear partial differential equations, and the source iterms in the equations are handled delicately.

Key words: Solid rocket engine;Jet nozzle;Axisymmetric flow;Flow field