摘要
对典型高超声速二元进气道二维流场进行了数值分析,研究了高超声速进气道不起动和再起动过程,发现当高超声速进气道不起动发生后,加大来流马赫数到起动马赫数,进气道不能立即再起动,继续加大来流马赫数到一定数值时,进气道可以再起动,但再起动马赫数远大于起动马赫数,小于设计马赫数。同时还发现高超声速进气道再起动过程也存在迟滞回路现象,但不同于常规进气道的再起动特性。
The flow in a typical 2D hypersonic inlet was analyzed with three-dimensional numerical analyzer. The flow characteristics of the inlet in the restarting process were discussed. In the numerical simulation of restating process of the inlet, the calculation of the restarting flow of the inlet is done based on the unstarting flow of the inlet with the increase of Mach number of inflow gradually. The result shows that with the increase of Mach number of the inflow, the inclined backward shock wave standing in the front of the inlet due to inlet unstart moves to the entrance of isolator and the strength of the separation bubble behind the shock gets gradually smaller. The flow in hypersonic inlet still holds at unstarting state even if the Mach number of inflow increases to the starting Mach number. With further increase of Mach number of inflow, the inclined backward shock wave and the separation bubble behind the shock disappears finally and the inlet restarts. The restarting Mach number is far greater than the starting Mach number, but a little smaller than the design Mach number of the inlet.
出处
《推进技术》
EI
CAS
CSCD
北大核心
2006年第5期390-393,398,共5页
Journal of Propulsion Technology
基金
国家"八六三"项目(2004AA723020)
关键词
高超声速进气道
起动
数值仿真
Hypersonic inlet
Starting
Numerical simulation
