The flow and heat transfer characteristics of a film jet inclined to different supersonic situations with a varying Mach number of the main flow were numerically investigated. In supersonic situations, complicated waves are generated by the obstacle of the film jet. In this work, extra pressure is exerted onto the film jet, causing better film attachment to the wall. The strengthening of attachment decreases mixing between the main flow and film jet, causing better film cooling. We observed multi-interfacial layered structures caused by the film jet under the complicated effect of shock waves. At the interfaces of the film jet and shock waves, additional pressure is exerted on the film towards the wall. The pressure increases as the Mach number of the main flow increases and contributes to the increased adhesion of the gas film, which causes the cooling enhancement under a supersonic condition. In the vicinity of the film hole exit, a local low pressure region is formed under the influence of the supersonic main flow. An aerodynamic convergent–divergent state was formed in the film hole, devastating the state of supersonic congestion of the film hole and further enhancing the film cooling effect.

中文翻译：

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超声条件下主流马赫数对薄膜冷却特性的影响

数值研究了具有不同马赫数的不同超声速条件下倾斜的薄膜射流的流动和传热特性。在超音速情况下，胶片射流的障碍会产生复杂的波。在这项工作中，额外的压力施加在胶片喷口上，从而使胶片更好地附着在墙上。附件的加强减少了主流与薄膜射流之间的混合，从而改善了薄膜的冷却。我们在冲击波的复杂作用下观察到了由薄膜射流引起的多界面分层结构。在薄膜射流和冲击波的界面处，薄膜会向壁施加额外的压力。压力随着主流的马赫数增加而增加，并有助于增加气膜的附着力，在超音速条件下会增强冷却效果。在膜孔出口附近，在超音速主流的影响下形成局部低压区域。在薄膜孔中形成了气动的收敛-发散状态，破坏了薄膜孔的超音速拥挤状态，并进一步增强了薄膜的冷却效果。