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为了探寻内压缩段构型对高超声速进气道自起动性能的影响,对二元高超声速进气道折角型和曲线型两种内压缩段的自起动过程进行准定常数值仿真研究.对比了这两种构型进气道在不同唇罩起始压缩角下的自起动性能和自起动过程中分离区的变化规律,并分析了内通道压缩强度沿程分布对进气道自起动性能的影响.研究表明:(1)即使进气道内收缩段的内收缩比相同,不同的内压缩段构型和唇罩起始压缩角对高超声速进气道的自起动性能影响显著,曲线型内压缩段构型的自起动性能明显优于折角型;(2)内压缩段的总压缩强度及其沿流向分布都是影响高超声速进气道自起动性能的关键因素,并且压缩强度沿流向分布决定着进气道在自起动过程中处于临界状态下主分离包所停留的位置.
In order to explore the influence of internal compression section configuration on the self-starting performance of the hypersonic inlet, the quasi-steady-state simulation of the self-starting process of the two internal compression sections of the two-dimensional supersonic inlet was carried out. The self-starting properties and the changing rules of the separation zone of the two kinds of air intakes under the initial compression angle of the lip are analyzed. The distribution of the compressive strength of the inner channel along the self-starting process is analyzed. .The results show that: (1) Different inner compression configurations and initial lip compression angle have significant effects on the self-starting performance of the hypersonic inlet even though the internal contraction ratio of the contraction section in the inlet is the same, (2) The total compressive strength of the internal compression section and the distribution along the flow direction are the key factors affecting the self-starting performance of the hypersonic inlet, and the compressive strength distribution along the flow direction Determines the position at which the main separation bag stays in the critical state of the inlet duct during the start-up.