火箭燃气喷流与弹体超声速绕流干扰流场数值分析

推进技术 ›› 1999, Vol. 20 ›› Issue (3): 17-20.

火箭燃气喷流与弹体超声速绕流干扰流场数值分析

鞠玉涛,郑亚

南京理工大学机械学院;南京理工大学机械学院

发布日期:2021-08-15

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

School of Machinery,Nanjing Univ.of Science and Technology,Nanjing,210094;School of Machinery,Nanjing Univ.of Science and Technology,Nanjing,210094

Published:2021-08-15

摘要/Abstract

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。

关键词: 火箭发动机;超声速尾流;纳维尔－斯托克斯方程;数值模拟;尾流干扰

Abstract: 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.

Key words: Rocket engine;Supersonic wake;Navier Stockes equations;Numerical simulation;Wake interaction

鞠玉涛,郑亚. 火箭燃气喷流与弹体超声速绕流干扰流场数值分析[J]. 推进技术, 1999, 20(3): 17-20.