摘要
对一系列不同收缩比、不同波系配置的内压缩通道二维流场进行了数值模拟。研究了面积收缩比、飞行高度和来流攻角对高超声速进气道起动性能的影响,提出了进口起动马赫数和来流起动马赫数的概念。研究表明,当进气道收缩比增大时,进气道的进口起动马赫数增大;来流起动马赫数由外压波系强度和进口起动马赫数决定,所以来流攻角变化改变外压波系强度,从而改变来流起动马赫数;随着飞行高度的增加,来流起动马赫数和进口起动马赫数增大,造成这一变化的原因是飞行高度不同,来流雷诺数不同,造成收缩段进口截面附面层厚度不同。
The unstart phenomena is one of the most important issue in the hypersonic inlets. The deep understand for the effects of starting ability of hypersonic inlets is very important to the design of hypersonic inlets. A series of inner contraction tunnel with different area contraction ratio and different waves were designed in this paper. The flows were simulated with NS equation and the facts which effects the starting ability of the hypersonic inlet were investigated. The starting mach number of inflow and the starting Mach number at the entrance of the inlet were defined. The result shows that with the increase of the inner contraction ratio, the starting Mach number of inflow is increases. The starting Mach number at the entrance of the inlet depend on the area contraction ratio ,the thickness of boundary layer at the entrance of the inlet and total pressure recover in the inner contraction tunnel. The starting Mach number of inflow depend on the strength of shock wave out of entrance of the inlet and the start Mach number at the entrance of the inlet . The start Mach number of inlet is affect by the angle of attack and fling attitude through change of the thickness of boundary layer.
出处
《宇航学报》
EI
CAS
CSCD
北大核心
2006年第4期714-719,共6页
Journal of Astronautics
基金
国家863高技术项目(2004AA723020)
