升力体外形高超声速边界层转捩红外测量实验  

Infrared thermogram measurement experiment of hypersonic boundary-layer transition of a lifting body

作　　者：陈久芬[1] 徐洋 蒋万秋[1] 凌岗[1] 段茂昌 张毅锋[2] CHEN Jiufen;XU Yang;JIANG Wanqiu;LING Gang;DUAN Maochang;ZHANG Yifeng(Hypervelocity Aerodynamics Institute,China Aerodynamics Research and Development Center,Mianyang 621000,China;Computational Aerodynamics Institute,China Aerodynamics Research and Development Center,Mianyang 621000,China)

机构地区：[1]中国空气动力研究与发展中心超高速空气动力研究所,绵阳621000 [2]中国空气动力研究与发展中心计算空气动力研究所,绵阳621000

出　　处：《实验流体力学》2024年第5期98-106,共9页Journal of Experiments in Fluid Mechanics

基　　金：国家自然科学基金项目(11872370);国家重点研发计划项目(2016YFA0401200)。

摘　　要：在常规高超声速风洞中,开展了针对升力体模型的边界层转捩红外测量实验,研究了不同单位雷诺数和马赫数对升力体边界层转捩的影响规律,并与eN方法计算结果进行了对比。实验模型长度为800 mm,来流单位雷诺数为0.46×10^(7)~3.94×10^(7)m^(–1),马赫数为5~8,迎角为0°。通过大面积红外热图技术获得了模型表面温升分布,得到了边界层转捩阵面形状。实验结果表明:在升力体边界层中存在横流失稳和第二模态转捩;随着单位雷诺数增大,横流转捩效应增强,模型下表面和上表面温升增大,转捩阵面前移,转捩区域扩大;随着马赫数增大,横流转捩效应减弱,转捩位置后移,转捩区域显著减小;不同单位雷诺数和马赫数下的转捩N值比较接近,但上、下表面的转捩N值不同(下表面约为6,上表面约为2.5),侧缘在高单位雷诺数下会出现高频第二模态转捩。For a lifting body model,the boundary layer transition infrared thermogram measurement experiment was carried out in the conventional hypersonic wind tunnel,and the influence of different unit Reynolds number and Mach number on the lifting body boundary layer transition was studied,which was compared with the calculation results of the eN method.The length of the experimental model is 800 mm,the unit Reynolds number is 0.46×10^(7)–3.94×10^(7)m^(–1),the Mach number is 5–8,and the angle of attack is 0°.The transition position and transition front of the boundary layer on the surface of the model are obtained by the large-area infrared thermogram technology.The analysis of the experimental results shows that there are crossflow instability and the second mode transition in the boundary layer of the lifting body.As the unit Reynolds number increases,the crossflow transition effect increases,the temperature rise on the lower and upper surfaces of the model increases,the transition front moves forward,and the transition area expands;as the Mach number increases,the crossflow transition effect gradually weakens and the transition position moves downstream,and the transition area significantly shrinks back.Moreover,the transition N factor at different Mach numbers and unit Reynolds numbers are relatively close,but the N factors of the upper and lower surfaces are different.The lower surface is about 6,and the upper surface is about 2.5.The high-frequency second mode transition occurs in the side edge at high unit Reynolds numbers.

关 键 词：升力体 高超声速风洞 边界层转捩 红外热图 e^(N)方法 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程]