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结合简单一维流理论讨论了一种工作于Ma=4～7、采用可转动唇口的变几何二元高超声速进气道设计方案,并利用数值仿真手段对其Ma=4下的自起动性能及其他不同工作马赫数下的性能进行了研究.结果表明:所设计的变几何进气道必须辅以附面层排移措施才能在Ma=4下顺利实现自起动;该变几何方案Ma=4下的流量系数达0.7以上,这为飞行器加速提供了强有力保障;与定几何进气道相比,变几何进气道高低马赫数下的总体性能均得到显著提高;此外,转动唇口的铰接位置对自起动性能有重要影响.
A kind of variable geometry bivariate hypersonic air inlet design with Ma = 4 ~ 7 and revolvable lip was discussed based on the simple one-dimensional flow theory. The numerical simulation was applied to the self-starting under Ma = 4 Performance and other Mach performance under different working conditions were studied.The results show that the design of the variable geometry inlet must be accompanied by the formation of the tailing displacement in order to successfully achieve the start under Ma = 4; the variable geometry Ma = 4 under the flow coefficient of 0.7 or more, which provides a strong guarantee for the aircraft accelerates; compared with the fixed geometry inlet, variable geometry Mach number of inlet height are significantly improved overall performance; In addition, the rotating lip The articulation of the mouth has a significant influence on the self-starting behavior.