分布式烧蚀形貌对高超声速平板边界层不稳定性影响

doi:10.7527/S1000-6893.2024.30464

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分布式烧蚀形貌对高超声速平板边界层不稳定性影响

李学良¹,李创创¹,张亚寒¹,苏伟²,吴杰¹

1. 华中科技大学
2. 北京航天长征飞行器研究所

收稿日期:2024-03-29 修回日期:2024-06-24 出版日期:2024-06-25 发布日期:2024-06-25
通讯作者: 吴杰

Effect of distributed ablation pattern on hypersonic flat plate boundary-layer instability

Received:2024-03-29 Revised:2024-06-24 Online:2024-06-25 Published:2024-06-25
Contact: Jie Wu

摘要/Abstract

摘要： 高超声速飞行器表面的热防护材料在经历高温烧蚀后，呈现出分布式粗糙元形貌，而这种形貌对高超声速边界层转捩的影响规律和机制目前尚无统一认识，引起转捩研究人员的重视。本文基于华中科技大学Φ0.5 m马赫6 Ludwieg管风洞开展了风洞试验，研究了光滑和四种高度为h=0.5，1.0，1.5，2.0 mm分布式粗糙元表面工况下高超声速平板边界层内不稳定波的演化规律，开展了单位来流雷诺数5.39×106 m-1~1.72×107 m-1系列来流工况研究，明晰了分布式粗糙元高度因素和来流雷诺数对平板边界层不稳定性的影响。试验结果表明，在分布式粗糙元工况下，主导边界层不稳定性的仍为第二模态不稳定波，频率范围约位于60~120 kHz。对于高度低于当地边界层厚度的分布式粗糙元，高度因素对高超声速平板边界层的转捩位置影响较小。分布式粗糙元高度对高超声速平板边界层内第二模态不稳定波沿流向传播速度的影响是非单调性的，存在影响最大的临界高度。不同雷诺数来流条件下，光滑工况和粗糙工况下的第二模态波特征演化规律基本一致，且不同高度粗糙元工况在相同来流雷诺数下的边界层转捩位置区别不大。

关键词: 高超声速, 烧蚀形貌, 边界层转捩, 不稳定性, 平板模型, 风洞试验

Abstract: After experiencing high-temperature ablation, the thermal protection material on the surface of hypersonic vehicle exhibits a pattern of distributed roughness element. However, the effect of such pattern on hypersonic boundary layer transition and its influencing mechanism have not been recognized at present, which has attracted the attention of transition researchers. In this study, wind tunnel experiments are carried out based on the Φ0.5m Mach 6 Ludwieg tube wind tunnel of Huazhong University of Science and Technology. The evolution of instability waves in the hypersonic boundary layer of the flat plate is studied in the cases of smooth and distributed roughness elements with four heights of h= 0.5, 1.0, 1.5 and 2.0 mm, and various of Reynolds number at 5.39 × 106 m-1~ 1.72 × 107 m-1. The effects of distributed roughness element height and incoming Reynolds numbers on the boundary layer instability of a flat plate are clarified. The experimental results show that the second mode instability waves dominate the instability of the hypersonic boundary layer in the cases of distributed roughness element, and the frequency range is about 60~120 kHz. For the distributed roughness element which is lower than the local bounda-ry layer thickness, it has obvious effect on the base flow in the boundary layer, but the height factor has little influ-ence on the transition position of the hypersonic boundary layer. The influence of the distributed roughness ele-ment height on the flow velocity of the second mode instability waves in the hypersonic plate boundary layer is non-monotonic, and there is a critical height that has the greatest influence. Under different Reynolds number inflow conditions, the characteristic evolution of the second mode instability waves in the smooth case and roughness case is basically the same, and the boundary layer transition position of different height roughness cases has little difference under the same Reynolds number.

Key words: hypersonic, ablation pattern, boundary layer transition, instability, flat plate model, wind tunnel experiment

中图分类号:

V211.7

李学良李创创张亚寒苏伟吴杰. 分布式烧蚀形貌对高超声速平板边界层不稳定性影响[J]. 航空学报, doi: 10.7527/S1000-6893.2024.30464.

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分布式烧蚀形貌对高超声速平板边界层不稳定性影响

Effect of distributed ablation pattern on hypersonic flat plate boundary-layer instability

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