Abstract: Flow separation phenomenon exists in the nozzle of the high altitude rocket engine when it was tested at the grownd.Numerical simulation was carried out for the flow separation in overexpanded rocket nozzle using Beam Warming approximate factorization method to solve thin layer N S equations.The location of Separation region and distribution of wall pressure in the nozzle were predicted.These will be the references of high altitude rocket engine test and provided basis for studying the influence factors of flow separation

Key words: Flow distribution;Navier Stockes equations;Approximate solution;Nozzle;Numerical simulation

摘要： 针对高空喷管地面试验时产生流动分离的现象，用Ｂｅａｍ －Ｗａｒｍ ｉｎｇ 近似因式分解法求解薄层Ｎ－Ｓ方程，对分离流场进行数值模拟。预示了分离点的位置以及喷管壁面压强分布等，可以为高空发动机地面试车提供参考， 并为进一步研究分离的影响因素打下基础

关键词: 流动分布;纳维尔-斯托克斯方程;近似解法;喷管;数值仿真