摘要
针对某包含引射、亚燃两模态（马赫数为0～4．0）的支板式火箭基组合循环（rocket based combinedcycle）发动机地面集成试验，设计了样机用带支板的二元进气道．数值模拟对比分析了在亚燃模态下进气道加入支板前后的性能以及流道内的流动情况，验证了设计的合理性，并且给出了支板位置以及构型的改变引起RBCC发动机进气道性能变化的规律和优化设计结果．
The inlet of RBCC （rocket based combined cycle） engine ground-test proto- type operated in rocket ejector mode and ramjet mode （Mach number from 0 to 4.0） was investigated. The 2 D （two-dimentional） inlet with strut was designed. Through numerical simulation, a comparative analysis of the performance and the inner flow with/without strut in the inlet in ramjet mode was made, whereas rationality of the design was verified and a rule was derived for the variation of the performance of RBCC prototype＇s inlet, which was induced by the change of the location or the configuration of strut. Finally, an optimized configuration was obtained.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2011年第8期1801-1807,共7页
Journal of Aerospace Power
关键词
支板式火箭基组合循环
二元进气道
支板
设计
数值模拟
RBCC （rocket based combined cycle）
2-D （two-dimentional） inlet
strut
design
numerical simulation
