摘要
从二维欧拉方程出发 ,采用非结构网格技术对固体火箭发动机内流场进行数值模拟 ,研究了点火初期、燃烧过程中和燃烧结束时固体火箭发动机燃烧室不规则物理区域内形成的复杂流动 ,分析了流场结构及特性 。
Based on Euler equations,inner flow field of solid rocket motor is studied by using unstructured grid technology.The irregular regions on the whole process of combustion are simulated numerically and the structures of flow field are analyzed.The problems with unsturctured grid to simulate such flow field are also discussed.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2001年第4期9-11,共3页
Journal of Solid Rocket Technology
