航空学报2025，Vol.46Issue(2)：69-89,21.DOI:10.7527/S1000-6893.2024.30464
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 boundary-layer instability with a flat plate
李学良 1李创创 1张亚寒 1苏伟 2吴杰1
作者信息
- 1. 华中科技大学 航空航天学院,武汉 430074
- 2. 北京航天长征飞行器研究所,北京 100076
- 折叠
摘要
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 bound-ary layer transition and its influencing mechanism have not been recognized at present,which has attracted the atten-tion of researchers.Wind tunnel experiments are carried out based on the ∅0.5 m Mach number 6 Ludwieg tube wind tunnel of Huazhong University of Science and Technology.The evolution of instability waves in the hypersonic bound-ary layer of the flat plate is studied in the cases of smooth and distributed roughness elements with four heights of 0.5,1.0,1.5,2.0 mm and various of Reynolds number at 5.39×106 m-1 to 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 bound-ary layer in the case of distributed roughness element,and the frequency range is about 60 kHz to 120 kHz.For the distributed roughness element which is lower than the local boundary layer thickness,the height factor has little influ-ence on the transition position of the hypersonic boundary layer.The influence of height of the distributed roughness element 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 the inflow conditions of different Reyn-olds numbers,the characteristic evolution of the second mode instability waves in the smooth and roughness cases is basically the same,and the boundary layer transition positions of roughness elements at different heights have little dif-ference with the inflow of the same Reynolds number.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Key words
hypersonic/ablation pattern/boundary layer transition/instability/flat plate model/wind tunnel test分类
航空航天引用本文复制引用
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,2025,46(2):69-89,21.
