超音通流进气道计算内特性

CALCULATED INTERNAL PERFORMANCE OF THE SUPERSONIC THROUGH FLOW INLET

计算模拟了一种无亚音扩压段的非常规形式进气道──超音通流（ＳｕｐｅｒｓｏｎｉｃＴｈｒｏｕｇｈＦｌｏｗ或ＳＴＦ）进气道的内流特性。其中对Ｓｅｄｄｏｎ和Ｇｏｌｄｓｍｉｔｈ提出的进气道激波与附面层干扰损失计算模型中的权因子，Ｇ扩展了定义，使该模型可用于口内通道总趋势收缩的超音通流进气道。所得飞行Ｍａ为０～２．７的损失特性等曲线，首次揭示了此类进气道的典型特征。数值上满意验证了文献的预估。

A calculating model for simulating the internal performances of an unconventional in- let-Supersonic Through Flow Inlet being dismounted the subsonic diffuser.The model extended the definition of weight factors Q and G in the estimating equation for inlet’s boundary layer-shook interference loss proposed by Seddon and Goldsmith,So that the model can be used for inlets with a convergent internal duct such as here the Supersonic Through Flow Inlet. With curves such as losses and flow quantity supply about flying Mach number 0～2.7,the result illustrated for the first time this type of inlet’s characteristics.The model and data available will benefit a thorough study of some kinds of advance coneeived propulsion systems.