摘要
对不同来流马赫数及不同反压下等直隔离段的出口温度、压力和马赫数进行了分析.通过曲线拟合,得到了不同反压下隔离段出口温度、压力及马赫数间的拟合式,据此给出了预估任意反压下,隔离段出口马赫数和温度的方法;研究了隔离段最大承受反压与无反压下隔离段出口马赫数的关系,分别给出了均匀来流和非均匀来流时隔离段最大承受反压的拟合关系式,为最大反压比的估算提供了方法;同时还给出了均匀来流条件下等直隔离段长高比的工程选取拟合式.
The flow filed in the isolator of a typical hypersonic inlet was simulated with uniform and non-uniform(with oblique shock) inflow.The pressure-temperature-Mach number at isolator exit relationship was investigated,the relationship of each other was presented,and all of those were independent of the isolator length.The predicting methods of the performance for constant area isolator under back pressure were studied,and doable predicting method of isolator under back pressure was presented.The concept of max...
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2009年第11期2421-2428,共8页
Journal of Aerospace Power
基金
国家863计划(2005AA723020)
关键词
高超声速推进系统
隔离段
隔离段性能预估
最大承受反压
hypersonic propulsion system
isolator
predicting method of the performance
maximum pressure capability
