摘要
本文对四侧30°进气并带有进气管道和尾喷口的突扩燃烧室冷态气流场进行了数值模拟.对这种复杂非规则边界的计算区域,首次采用分段算法进行计算.结果表明:分段算法可以提高网络利用率,缩短机时,消除虚假扩散,提高计算准确度,计算结果与试验结果基本符合.
A numerical simulation of cold flow field in a dump combustor with four 30-degree side inlet and a nozzle is presented in this paper. The segment calculation method is first used for this kind of calculation with complex configuration boundary. The research shows that the segment calculation method can increase the grid utilization, reduce the computation time, eliminate the false diffusion and raise the computational precision. Computational results are fundamentally in accordance with the experimental data.
出处
《推进技术》
EI
CAS
CSCD
北大核心
1989年第5期13-18,共6页
Journal of Propulsion Technology
关键词
冲压发动机
突扩型
燃烧室
流场
数值模拟
Integrate rocket ramjet, Dump combustion chamber, Flow field, Calculation method
