Abstract: Impinging jet produced by launching missile was numerically simulated by using NND2M difference scheme which was simple structure and efficient to use The computation was based on the Navier Stokes equations The computational results were well agreement with the experimental results Then the flow structure was studied

Key words: Missile propulsion;Engine exhaust;Plume;Jet enterference;Numerical simulation

摘要： 采用计算流体力学方法,从曲线坐标NS方程出发,取用NND2M差分格式,对导弹发射时与地面形成碰撞喷流流场进行数值模拟,计算结果和实验数据符合较好。在此基础上,分析了碰撞喷流的流场结构及特性。

关键词: 导弹推进;发动机排气;羽流;喷流干扰;数值仿真