基于弯曲激波压缩系统的高超声速进气道反设计研究进展  

Research progress of hypersonic inlet reverse design based on curved shock compression system

作　　者：张堃元[1] 

机构地区：[1]南京航空航天大学能源与动力学院江苏省航空动力系统重点实验室,南京210016

出　　处：《航空学报》2015年第1期274-288,共15页Acta Aeronautica et Astronautica Sinica

基　　金：国家自然科学基金(90916029)~~

摘　　要：总结了近十年来弯曲激波压缩研究的主要成果。提出了弯曲激波压缩系统的新概念,即利用特殊设计的楔形弯曲压缩面或空间弯曲压缩面,产生一系列与前缘弱激波相互交汇或叠加的压缩波系,从而使前缘激波弯曲,形成特殊的弯曲激波,它与波后的等熵压缩波来共同完成对气流的压缩。在此基础上,实现了由给定出口气动参数的超声速内流道反设计,实现了由给定压缩面压力分布和给定压缩面马赫数分布要求的型面反设计,实现了由给定激波波面的压缩型面反设计。研究证明,弯曲压缩面-弯曲激波压缩系统具有良好的综合气动性能,为高性能高超声速进气系统的气动设计提供了一种全新的设计方法。This paper gives a summary on curved shock compression research in the last decade. The new concept of curved shock compression system is proposed, in which specially designed 2D or 3D curved compression surface is applied, The leading shock wave would be curved due to its interaction with isentropic compression waves near the compression surface, and free stream is compressed by the curved shock wave together with the isentropic waves. Based on this concept： methods of reverse designing supersonic internal flow path according to assigned outflow parameters, reverse designing compression surface according to pressure distribution or Mach number distribution along the surface, and reverse designing surface according to shock wave shape are established. The curved shock compression has a good comprehensive performance as shown in the investigation, and represents a brand-new approach for the design of hypersonic propulsion compression system.

关 键 词：高超声速进气道 反设计 弯曲激波压缩系统 弯曲压缩面 风洞试验 变几何进气道 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]