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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 flow tube compression and the critical total pressure recovery factor of supersonic inlet, an example of different flow Mach number and various schemes was taken as an example in the case of double wedge external pressure inlet. The Mach numbers range from 2.0 to 4.0 and various compression schemes involve a wide range of total turn angles and multiple combinations of wedge angles. The results show that the critical total pressure recovery coefficient has a significant positive correlation with the shrinkage ratio of the flow tube in terms of the range of compression schemes commonly used in the design. The two models show an approximately linear relationship within a certain range. Based on the flow tube Contraction ratio can be achieved on the critical total pressure recovery coefficient approximate judgment.