摘要
采用矢通量分裂法对非对称型二维ＤＣＲ进气分流流场进行了数值模拟，通过求解ＮＳ方程组，获得了全场清晰的物理图象，文中对计算结果进行了分析讨论。
A nonsymmetric 2-D Dual Combustor Ramjet (DCR) division-flow inlet field is simulated numerically with flux vector splitting method. By solving N--S equations a clear physical image of the whole field is obtained. The computation results are also analyzed and discussed.
出处
《推进技术》
EI
CAS
CSCD
北大核心
1995年第4期14-19,共6页
Journal of Propulsion Technology
基金
国家自然基金
关键词
亚音速燃烧
超音速燃烧
冲压喷气发动机
Subsonic combustion
Supersonic combustion
Ramjet engine
Flow distribustion
Numerical simulation
