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。
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.
出处
《推进技术》
EI
CAS
CSCD
北大核心
1999年第3期17-20,共4页
Journal of Propulsion Technology
关键词
火箭发动机
超声速尾流
绕流
尾流干扰
N-S方程
Rocket engine,Supersonic wake,Navier Stockes equations,Numerical simulation,Wake interaction
