一种新型内乘波式进气道初步研究

Investigation of internal waverider-derived hypersonic inlet

关键词:  高超声速  内乘波式进气道+  设计

Key words:  Hypersonic  Internal waverider-derived Inlet~+  Design

摘要:

提出了内乘波式进气道的设计概念。该进气道以内收缩锥轴对称流场为基础,采用流线追踪技术并截取激波面生成。它具有设计状态流量捕获能力强;三维压缩效率高;波系结构简单且无复杂角部流动,流动损失小等特点。采用该概念设计了来流马赫数6的内乘波式进气道,CFD计算结果显示:粘性对该类进气道设计具有较大影响,附面层的发展会使按无粘条件设计的进气道性能有所下降。尽管还没有进行粘性修正,在相同设计马赫数条件下,内乘波式进气道压比、流量系数和总压恢复系数等性能高于某典型侧压式进气道。

Abstract:

A kind of new hypersonic inlet which is internal waverider-derived hypersonic inlet is presented.It is based on an asymmetric internal compression flowfield like a funel and derived with the technology of streamtracing and shock-cutting.This kind of inlet is able to work with little spillage in its design condition and has great compression ability and high total pressure recovery due to its simple three dimensional shock structure.A sample Mach 6 internal waverider-derived inlet was designed with this concept and the CFD result showed that the development of boundary layer would drop down the performance of this inlet.However,the inlet without boundary layer correction yet still had better performance than a specified hypersonic side-wall inlet.