摘要
绕弹体的超音速气流与火箭发动机燃气喷流相互作用，在弹体底部形成了复杂的干扰流场。本文应用了四阶的ＭＵＳＣＬＴＶＤ格式，求解雷诺平均的ＮＳ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的变化规律。
The interaction between supersonic external flow and an exhaust jet results in a complex flowfield region near the missile afterbody.In this paper,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 ration were obtained.
出处
《固体火箭技术》
EI
CAS
CSCD
1999年第1期11-14,共4页
Journal of Solid Rocket Technology
关键词
尾流干扰
射流
数值模拟
超音速
弹体绕流
导弹
wake interaction
jet flow
Navier Stokes equation
numerical simulation
