摘要
对某构型三维侧压高超声速进气道开展了Ma4的自由射流试验和数值仿真,研究了低马赫数下不启动流场的流动机理。观测到了具有"对涡"结构的底板油流图案,并得到了分离区的范围和内部流动特征。分析得出,"对涡"结构油流图案和流场中部分离区的形成是唇口激波和内收缩形成的逆压梯度作用于侧板激波形成的流场中部低能流区的结果。根据试验和数值模拟结果给出了流场结构示意图,并为下一步进气道构形设计和性能改善工作提出了建议。
A three-dimensional sidewall compression hypersonic inlet was tested in Ma4 free-jet wind tunnel and examined by numerical simulation to investigate the characteristics of unstart flowfield at low Mach number. A ＂counter vortex＂ structural oil flow pattern was observed on the bottom wall. The result reveals that the reverse pressure gradient caused by cowl shock and internal compression, and the low kinetic energy flow near the bottom wall induced by sidewall swept shock, are the two factors that lead the separation bubble located at the center of the flow path. Schematic structure of the unstart flowfield and suggestion on the inlet design are obtained through the investigation.
出处
《宇航学报》
EI
CAS
CSCD
北大核心
2008年第6期1927-1931,2000,共6页
Journal of Astronautics
