高超侧压式进气道参数分析及试验研究

推进技术 ›› 1995, Vol. 16 ›› Issue (6): 20-25.

高超侧压式进气道参数分析及试验研究

张堃元,萧旭东,徐辉

南京航空航天大学动力工程系;南京航空航天大学动力工程系;南京航空航天大学动力工程系

发布日期:2021-08-15

PARAMETRIC ANALYSIS AND EXPERIMENTAL INVESTIGATION ON SIDEWALL COMPRESSION INLET

Dept.of Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing,210016;Dept.of Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing,210016;Dept.of Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing,210016

Published:2021-08-15

摘要/Abstract

摘要： 分析了高超侧压式进气过第一、二溢流窗的溢流角随后掠角的变化规律，分析了溢流窗气流与主流相互作用而形成一道脱体曲面激波的原因，设计了侧压角为６°，后掠角３０°的直前缘及圆弧前缘两套高超侧压式进气道，在Ｍ５．３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起动性能及总体性能试验，试验发现大量附面层吸入不仅对起动性能有重大影响，而且对总压恢复影响也极大。

关键词: 高超音速;进气道;超音速燃烧;冲压发动机

Abstract: parametric analysis and experimental study on 3-D sidewall compression inlet are presented.The effect of swept angle on flow in the 1st and 2nd spillagewindows were investigated.The interaction of out flow from spillage window with freestream and formation of an un-attached spillage shock have been studied.Inlet modelswith leading edge sweep of 30 degree and with a curved leading edge have been testedin M5.3 wind tunnel at the condition of simulated forebody boundary layer.The experimental results indicated that the incoming flow non-uniformity has a dramatic effect onpressure recovery and starting performance of inlet unless the most of simulated boundary layer was removed.Under the test conditions the inlet with a curved leading edgeseems have better performance than that with a straight leading edge.

Key words: s: Hypersonic speed;Inlet;Supersonic combustion;Ramjet engine

张堃元,萧旭东,徐辉. 高超侧压式进气道参数分析及试验研究[J]. 推进技术, 1995, 16(6): 20-25.