The flow of an active thermal protection system exploiting subsonic counter-flow jets for wing leading edges of hypersonic vehicles is numerically studied on the basis of the three dimensional Navier-Stokes equations. The coolant air issuing from around the stagnation point as an array of three jets spreads over both the upper and the lower sides of the cylinder surface and about 40 ~ 60% cooling effectiveness is achieved in the range up to 5 degrees angle of attack despite the occurrence of various three-dimensional fluid-dynamic instabilities. The numerical scheme is second order accurate but simple inclusion of high order polynomial approximation in the reconstruction enables the capturing of finer structure of the flow field.

中文翻译：

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从暴露于高超声速空气动力加热的机翼前缘发出的三个亚音速逆流射流的阵列的ILES

在三维Navier-Stokes方程的基础上，对采用亚音速逆流射流的高超音速飞行器机翼前缘主动主动热保护系统的流动进行了数值研究。从停滞点附近散发出的冷却剂空气是由三个喷嘴组成的阵列分布在气缸表面的上侧和下侧，尽管攻角为5度，但在高达5度的迎角范围内仍可实现约40〜60％的冷却效率。各种三维流体动力学不稳定性的发生。该数值方案是二阶精确的，但是在重构中简单地包含高阶多项式逼近使得能够捕获流场的更精细的结构。