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采用数值仿真的方法研究了内转式进气道的流动特征。研究表明:设计状态在近壁面唇罩激波诱发了二次流,进而发展形成流向涡,造成低能流堆积,隔离段出口流场分布不均,消弱了进气道的抗反压能力。有攻角条件下,口面激波偏离唇罩前缘,激波形态发生改变,激波波面中部展向具有准二维特性,压缩面两侧气流压缩变弱,激波层变薄,出现局部膨胀区;有攻角条件下的无黏流场,在进气道压缩段形成三维流向涡,该流向涡促进高能高速气流向壁面迁移,改善了黏性条件下隔离段出口流场的均匀度。
The numerical simulation method is used to study the flow characteristics of the internal transitional inlet. The results show that the shock wave induced by the lips lip near the wall induces the secondary flow, and then the flow vortices develop, resulting in the accumulation of low-energy flow and the uneven flow field at the outlet of the isolation section, which weakens the anti-backpressure capability of the inlet duct. Under the condition of angle of attack, the facial shock wave deviated from the front edge of the lip mask and the shock wave morphology changed. The quasi-two-dimensional characteristic of the shock wave surface in the middle was quasi-two-dimensional. The airflow compression became weaker on both sides of the compression surface and the shock wave layer became thinner The local expansion zone, the non-stick flow field under the condition of angle of attack and the formation of three-dimensional flow vortices in the compression section of the inlet duct. The flow vortex promotes the migration of high-energy and high-velocity gas to the wall and improves the uniform flow field at the outlet of the isolation section under viscous conditions degree.