高超声速钝头体边界层转捩试验  

Hypersonic boundary layer transition over bodies with blunt nosetip

作　　者：陈苏宇[1] 江涛[1] 常雨[1] 胡守超[1] 李强[1] 张扣立[1] CHEN Suyu;JIANG Tao;CHANG Yu;HU Shouchao;LI Qiang;ZHANG Kouli(Hypervelocity 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

出　　处：《航空学报》2020年第12期206-214,共9页Acta Aeronautica et Astronautica Sinica

基　　金：国家重点研发计划(2016YFA0401201)。

摘　　要：为研究高超声钝头体边界层转捩以及头部钝度对转捩的影响,在FD-14和FD-14A两座激波风洞中开展了热流、压力扰动和高速纹影显示等综合测量。试验结果表明,转捩雷诺数关于钝度雷诺数的变化显示出转捩反转的趋势。压力扰动的功率谱密度(PSD)分析结果以流向离散分布云图形式显示,边界层高速纹影图像显示了第二模态波的发展、湍流的生成和熵层对边界层结构的显著影响。大头部钝度带来的强熵梯度熵层流动对边界层压力扰动频谱特性和流动结构影响显著,在转捩反转机理中起到重要作用。此外,马赫数对转捩的影响不容忽视。To investigate hypersonic boundary layer transition and the effect of nosetip bluntness on transition,this study carries out experiments in both FD-14 and FD-14 Ashock tunnels.Integrated measurements including heat flux measurement,pressure disturbances measurement,and high-speed schlieren visualization are conducted.Results show that the transition Reynolds number as a function of Reynolds number based on nosetip bluntness exhibits a trend of transition-reversal.Power Spectral Density(PSD)analysis of pressure disturbances in the boundary layer is shown in the form of discrete contour maps in a streamwise direction.Development of second-mode waves,generation of turbulence and effect of the entropy layer on the boundary layer structure are visualized in images of high-speed schlieren.The entropy layer with an intense entropy gradient derived from large nosetip bluntness shows significant influence on the frequency spectral of pressure disturbances and flow structures of the boundary layer,playing an important role in the mechanism of transition-reversal.In addition,the effect of the Mach number should not be ignored.

关 键 词：高超声速边界层转捩 压力扰动 头部钝度 转捩反转 熵层 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]