二元超声速进气道流管压缩量特性与应用初步研究  

Properties of Capture Stream Tube Contraction Ratio and Application of 2D Supersonic Inlet

作　　者：关祥东[1] 李宏东[1] 孟宇鹏[1] 朱守梅[1,2] 

机构地区：[1]北京动力机械研究所,北京100074 [2]北京动力机械研究所高超声速冲压发动机技术重点试验室,北京100074

出　　处：《推进技术》2013年第12期1616-1620,共5页Journal of Propulsion Technology

摘　　要：为研究流管压缩程度与超声速进气道临界总压恢复系数的规律,以双楔外压式进气道为例,对不同来流马赫数、多种方案进行实例研究。研究马赫数范围为2.0至4.0,各种压缩方案涉及宽泛的总转折角范围和多种楔角组合方式。研究结果表明,就通常设计中常用的压缩方案范围而言,临界总压恢复系数与流管收缩比呈明显的正相关变化规律,并在一定的范围内两者呈近似线性关系,基于流管收缩比可实现对临界总压恢复系数大小的近似判断。In order to study the regularity of capture stream tube contraction ratio and the critical total pressure recovery coefficient of 2D-surpersonic inlet, a large number of double wedges external compression inlets with various Ma∞ are investigated The inlets studied include various total external compression angle and a variety of wedge angle combination. The range of Ma~ is 2.0 to 4.0. Analyses indicate that the criti- cal total pressure recovery coefficient presents obviously positive relation with capture stream tube contrac- tion ratio in the commonly used range of total compression angles. In certain regions, a linear relation be- tween them is observed. The critical total pressure recovery coefficient can be estimated approximately using capture stream tube contraction ratio.

关 键 词：超声速进气道 临界总压恢复系数 二元进气道 

分 类 号：V235.213[航空宇航科学与技术—航空宇航推进理论与工程]