导弹尾喷流形成的碰撞流场数值模拟  

Numerical simulation of impinging jet produced by missile

作　　者：刘君[1] 张泰峰 陈宏[1] 

机构地区：[1]国防科技大学航天技术系,湖南长沙410073

出　　处：《推进技术》2000年第1期30-32,共3页Journal of Propulsion Technology

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。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

关 键 词：导弹推进 发动机排气 数值仿真 碰撞流场 CFD 

分 类 号：TJ760.11[兵器科学与技术—武器系统与运用工程] V430[航空宇航科学与技术—航空宇航推进理论与工程]