An array of subsonic counter-flow jets is studied as an active thermal protection system (TPS) for wing leading edges of hypersonic vehicles. The performance is numerically estimated in the model case of a circular cylinder on the basis of the 2D compressible Navier-Stokes equations. In contrast to a single subsonic jet, an array of jets is robust against variation of the angle of attack; high cooling effectiveness is confirmed up to 5° variation. The coolant gas (air) discharged from channels embedded in the cylinder covers over a wide range of the front surface of the cylinder. The feasibility of the active TPS is also discussed.

中文翻译：

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机翼前缘主动TPS的数值研究，该机翼前缘暴露在强弓冲击波后暴露于高温空气中

研究了一系列亚音速逆流射流，作为高超声速飞行器机翼前缘的主动热保护系统（TPS）。在圆柱模型的情况下，根据2D可压缩Navier-Stokes方程对性能进行数值估算。与单个亚音速喷气机相反，一系列喷气机对迎角的变化具有鲁棒性。确认高达5°的变化都具有很高的冷却效率。从气缸中嵌入的通道排出的冷却气体（空气）覆盖气缸前表面的很大范围。还讨论了主动TPS的可行性。