非均匀流等溢流角设计高超侧压进气道  

HYPERSONIC SIDEWALL COMPRESSION INLET WITH CONSTANT SPILLAGE ANGLE DESIGN AT NON UNIFORM INCOMING FLOW

作　　者：萧旭东[1] 徐辉[1] 

机构地区：[1]南京航空航天大学动力工程系

出　　处：《推进技术》1998年第1期20-24,共5页Journal of Propulsion Technology

基　　金：国家自然科学基金

摘　　要：工作在前体附面层内的高超侧壁压缩进气道，来流的非均匀性应该是进气道设计的一个重要依据。按经典的附面层理论和等溢流角设计准则设计了侧壁压缩角为６°，前缘型线为圆弧的变后掠角高超侧压式进气道模型，在Ｍａ５．３／Ｍａ４风洞中利用风洞壁面自然发展的附面层进行非均匀来流下进气道性能试验。试验发现，在相同的来流附面层条件下，圆弧前缘进气道相对于直前缘进气道喉道处的压力畸变小、进气道总压恢复高。Three dimensional sidewall compression inlet model with circle shaped leading edge under condition of non uniform supersonic incoming flow is designed and experimentally investigated.The leading edge design was based upon the criterion of a constant spillage angle when a typical boundary layer flow was swallowed by the inlet.Two inlet model has been tested in Ma5 3/Ma4 wind turnel.The model No 1 with leading edge sweep of 30° considered as a basic one.The model No 2 with a curved leading edge is specially designed for non uniform incoming flow.The experimental results indicated that model No 2 is better than the baseline configuration model No 1 in terms of pressure distortion index and total pressure recovery in performance.

关 键 词：高超声速 进气道 流场畸变 非均匀流 

分 类 号：V211.48[航空宇航科学与技术—航空宇航推进理论与工程]