非均匀来流对新型高超弯曲激波二维进气道的影响  

Investigation on a New Hypersonic Curved Shock 2-Dimensional Inlet Under Non-Uniform Coming Flow

作　　者：张林[1] 张堃元[1] 王磊[1] 南向军[1] 李永洲[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》2012年第3期338-345,共8页Journal of Propulsion Technology

基　　金：国家自然科学基金(90916029)

摘　　要：针对一种采用新型压升规律的曲面压缩面所设计的高超弯曲激波二维进气道,利用数值模拟方法研究了6种不同长度平板发展而来的非均匀流对其性能参数的影响,并和两种常规二维进气道吞非均匀来流的能力进行了比较,着重对比了设计Ma数下三种不同压缩形式进气道喉道截面的流场畸变程度。数值模拟结果表明,采用新型压升规律的高超弯曲激波二维进气道性能受来流气流不均匀性的影响较小,且喉道截面的流场畸变指数小,对非均匀来流具有一定的校正作用。Based on a two-dimensional hypersonic curved-shock inlet with curved compression surface designed by a new wall pressure distribution,investigation was carried out through numerical simulation about the performance under non-uniform flow developed from 6 flat plates with different length,and compared the capability of tolerance to non-uniform flow with two conventional 2-D inlet.Especially,comparison was performed for the throat section flow distortion degree of three different compression form inlets at the design Mach number.The results indicate that two-dimensional hypersonic curved-shock inlet with curved compression surface designed by new wall pressure distribution is slightly influenced by non-uniform flow.The flow distortion index of throat section is smaller and can adjust the non-uniform flow to certain extent.

关 键 词：超燃冲压发动机进气道 二维高超声速进气道 非均匀来流 弯曲激波 数值仿真 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]