摘要
利用SIMPLE方法数值求解层流N-S方程,模拟了具有移动边界的固体火箭发动机燃烧室内的三维流场。网格划分采用交错网格技术,流场计算时不进行网格划分,而是直接读取网格点的值,将网格划分与流场计算分开,解决了现有计算机内存不够的问题。计算获得了满意结果。
Three-dimensional propellant geometries results in three-dimensional internal gas flow computation. In this paper, 3-D flow field of a solid rocket motor chamber with moving boundary by numerically solving the laminar Novier-Stokes equations using SIMPLE method is simulated. The crisscross grid technique has been adopted. In flow computations, the mesh division is not conducted, only the grids values are read out directly. The problem of insufficient memory of present computer is solved by separating the mesh division from flow field calculation. A significant result has been achieved.
出处
《推进技术》
EI
CAS
CSCD
北大核心
1995年第5期59-64,共6页
Journal of Propulsion Technology
关键词
固体推进剂
火箭发动机
燃烧室
三维流场
Solid propellant rocket engine, Combustion chamber, Three dimensional flow , Numerical simulation