| 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。 |
| 关键词: 超声速进气道 临界总压恢复系数 二元进气道 |
| DOI： |
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| Properties of Capture Stream Tube Contraction Ratio and Application of 2D Supersonic Inlet |
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GUAN Xiang-dong1, LI Hong-dong1, MENG Yu-peng1, ZHU Shou-mei1,2
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(1. Beijing Power Machinery Institute,Beijing 100074,China;2. Science and Technology on Scramjet Laboratory,Beijing Power Machinery Institute,Beijing 100074,China)
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| Abstract: |
| 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 2.0to 4.0. Analyses indicate that the critical total pressure recovery coefficient presents obviously positive relation with capture stream tube contraction ratio in the commonly used range of total compression angles. In certain regions, a linear relation between them is observed. The critical total pressure recovery coefficient can be estimated approximately using capture stream tube contraction ratio. |
| Key words: Supersonic inlet Critical total pressure recovery coefficient, 2D inlet |
