弯曲激波压缩型面的设计及数值分析  

Design and numerical investigation of curved shock compression surface

作　　者：潘瑾[1] 张堃元[1] 金志光[1] 

机构地区：[1]南京航空航天大学能源与动力学院,江苏南京210016

出　　处：《推进技术》2008年第4期438-442,共5页Journal of Propulsion Technology

基　　金：国家"八六三"计划702专题(2003AA723020)

摘　　要：分别采用等压缩角和递增压缩角的小折线构成压缩型面。研究了二维均匀超声来流流过压缩面时的波后超声流场,结果表明,该方法能够形成弯曲激波且波后气流沿流向的壁面静压近似为等压力梯度,其等压力梯度程度取决于各小折线压缩角的配置。采用该方法生成的曲面压缩型面进气道附面层稳定性好,优于常规的平面压缩进气道。与二维常规平面压缩进气道相比,设计工况下,性能相当;非设计工况下,性能优于二维常规平面压缩进气道。Compression surfaces are designed by using short lines with equal compression angle or increasing compression angle. Two dimensional supersonic flow fields are investigated when incoming flows pass through the compression surfaces. The results show that the compression surfaces can shape curved shock and pressure gradient along the surfaces is nearly constant, but the magnitude of constant pressure gradient depends on arrangement of short lines. It is shown that inlets with the nonconventional compression surfaces are more advantageous in keeping the stability of boundary layer than that one with conventional compression surfaces and their performance are similar at design point, but at off design point, the performance of inlets with non-conventional compression surfaces are better.

关 键 词：超声速进气道 均匀超声速流 二维流 弯曲激波 附面层分离 数值仿真 

分 类 号：V235.11[航空宇航科学与技术—航空宇航推进理论与工程]