6°攻角尖锥高超声速边界层高频不稳定波实验研究  

Experimental study on high frequency unstable waves in hypersonic boundary layer with sharp cone at 6°angle of attack

作　　者：刘姝怡 陈坚强[1] 袁先旭[1] 熊有德 吴杰 LIU Shuyi;CHEN Jianqiang;YUAN Xianxu;XIONG Youde;WU Jie(State Key Laboratory of Aerodynamics,Mianyang Sichuan 621000,China;School of Aerospace Engineering,Huazhong University of Science and Technology,Wuhan 430074,China)

机构地区：[1]空气动力学国家重点实验室,四川绵阳621000 [2]华中科技大学航空航天学院,武汉430074

出　　处：《实验流体力学》2021年第6期1-7,共7页Journal of Experiments in Fluid Mechanics

基　　金：国家自然科学基金(92052301)。

摘　　要：边界层转捩对高超声速飞行器的气动力和气动热设计有重要影响。横流失稳通常是三维边界层转捩的主导因素,而在噪声环境下,第二模态不稳定波的影响也不容忽视。为深入理解带攻角情况下高超声速边界层的转捩机理,在Mach 6 Ludwieg管风洞中采用聚焦激光差分干涉仪(Focused Laser Differential Interferometer,FLDI)和高频压力脉动传感器(PCB)对6°攻角尖锥进行了边界层稳定性实验研究。实验结果显示,在尖锥边界层的不同周向位置存在高频不稳定波。通过功率谱分析和双谱分析,得到该不稳定波沿母线的变化情况以及该高频不稳定波与低频信号(20~40 kHz)之间存在的非线性相互作用。Transition plays an important role in the aerodynamic and aerothermal design of hypersonic vehicles.Generally,crossflow instability plays the dominant role in inducing transition in the three-dimensional boundary layer.However,in the noisy environment the influence of the second mode of the instability cannot be ignored.In order to obtain a better understanding of the development of crossflow in the hypersonic boundary layer,the measurement of instability waves in the boundary layer of a 7°half-angle sharp cone model with 6°angle of attack was carried out using focused laser differential interferometer(FLDI)and high frequency pressure fluctuation sensor(PCB)in Mach 6 Ludwieg tube tunnel.The experimental results show that the high-frequency unstable waves are detected at different circumferential positions.Through power spectrum and bi-spectrum analysis,the variation of the unstable wave along the generatrix and the nonlinear interaction between the high-frequency unstable wave and the low-frequency signal(20–40 kHz)are obtained.

关 键 词：高超声速边界层 聚焦激光差分干涉仪 横流不稳定性 第二模态不稳定波 

分 类 号：O355[理学—流体力学]