Abstract: The interaction between supersonic external flow and an exhaust jet forms a complex flowfield near the missile afterbody.The research about this interaction flows was completed with fourth order MUSCL TVD scheme to solve the Reynolds averaged N S equations.The flowfield structures observed and it’s relation with jet pressure ratio were obtained.

Key words: Rocket engine;Supersonic wake;Navier Stockes equations;Numerical simulation;Wake interaction

摘要： 绕弹体的超声速气流与火箭发动机燃气喷流相互作用，在弹底部形成了复杂的干扰流场。应用四阶的ＭＵＳＣＬＴＶＤ格式，求解雷诺平均的Ｎ－Ｓ方程，对这一复杂流动进行了数值模拟，得到了流场结构随不同喷口压力比的变化规律。

关键词: 火箭发动机;超声速尾流;纳维尔－斯托克斯方程;数值模拟;尾流干扰