Experimental investigation on supersonic film cooling of hypersonic optical dome under different nozzle pressure ratios

Sun, Xiaofeng; Ding, Haolin; Liu, Mingxing; Yi, Shihe; Zhao, Yili

doi:10.1016/j.ast.2023.108488

Cited by 13 publications

(1 citation statement)

References 18 publications

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“…效果的影响, 结果发现在凸曲率上的冷却效果要高于在平面和凹曲率壁面的情况. 过去有许多专家学者对超声速气膜冷却 [10][11][12][13][14][15][16][17] 进行了深入的研究. Lin 等 [13] 在不同静压比(ratio of static pressure, RSP, RSP = P c /P f 下, 其中 P c 为超声速气膜出口处的静压, P f 为自由来流静压), 通过分析下游的速度梯度变化, 揭示了RSP差异下混合过程的物理机制, 随着RSP增大, 有效冷却长度得到延长.…”

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Flow evolution of mixed layer on convex curvature wall under hypersonic conditions

Zhang,

Yi,

Liu

et al. 2024

Acta Phys. Sin.

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With the continuous upgrading of hypersonic vehicles, a new design requirement for imaging window is put forward, that is, conformal window to improve aerodynamic characteristics, which requires the supersonic cooling film and optical window to maintain the same curvature shape as the aircraft body.This paper investigates the mixed-layer flow evolution on a convex wall (CV). The flow field structure of the mixed layer is captured using a nanoparticle-based planar laser scattering technique in a Ma=6 hypersonic static wind tunnel, combined with fractal dimension to investigate the location of mixed-layer instability. Results of pressure, and impulse of compression (Ip) evolution along the flow direction were obtained using numerical simulation techniques. The results show that the total incoming pressure (P0) has a significant effect on the flow evolution of the mixed layer, and as P0 increases, the ratio of static pressure (RSP) decreases, the position of the mixed layer instability is delayed, and the flow velocity of the typical vortex structure increases. The presence of favorable gradients at the CV wall allows the pressure to drop along the flow direction, and the pressure is boosted when the supersonic air film along the tangential direction of the wall is in operating condition. However, as P0 increases, RSP decreases with it, and the lifting effect of the pressure on the CV decreases. The flow field is affected by the expansion effect of the CV, and Ip decreases along the flow direction. The supersonic air film can weaken the expansion effect on the CV and thus suppress the decrease of Ip. The change rate of Ip (ΔIp) is significantly affected by P0, in the range of bending impulse |IΦ|=0.191~3.62, ΔIp decreases from 178.67% to 12.02% when P0=0.5Mpa and ΔIp decreases from 40.38% to 5.64% when P0=1.0MPa. ΔIp decreases as |IΦ| increases, but the decrease weakens as P0 increases. The results reveal the flow evolution law of hypersonic mixed layer under the influence of convex curvature, and provide a certain reference for the shape design of hypersonic vehicle to achieve aerodynamic drag reduction and thermal protection characteristics.

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