火箭燃气喷流与弹体超声速绕流干扰流场数值分析  

NUMERICAL STUDIES FOR INTERACTION FLOWFIELD BETWEEN SUPERSONIC FLOW AROUND BODY AND JET FLOW EXHAUSTING FROM ROCKET

作　　者：鞠玉涛[1] 郑亚[1] 

机构地区：[1]南京理工大学机械学院

出　　处：《推进技术》1999年第3期17-20,共4页Journal of Propulsion Technology

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.

关 键 词：火箭发动机 超声速尾流 绕流 尾流干扰 N-S方程 

分 类 号：V430[航空宇航科学与技术—航空宇航推进理论与工程]