| 6°攻角尖锥高超声速边界层高频不稳定波实验研究 |
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| 引用本文： | 刘姝怡,陈坚强,袁先旭,熊有德,吴杰.6°攻角尖锥高超声速边界层高频不稳定波实验研究[J].实验流体力学,2021,35(6):1-7. |
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| 作者姓名： | 刘姝怡 陈坚强 袁先旭 熊有德 吴杰 |
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| 作者单位： | 1.空气动力学国家重点实验室，四川 绵阳 621000 |
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| 基金项目： | 国家自然科学基金（92052301） |
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| 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。
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| 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 |
| 收稿时间： | 2021-06-10 |
Experimental study on high frequency unstable waves in hypersonic boundary layer with sharp cone at 6° angle of attack |
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| Affiliation: | 1.State Key Laboratory of Aerodynamics, Mianyang Sichuan 621000, China2.School of Aerospace Engineering, Huazhong University of Science and Technology, Wuhan 430074, China |
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| Abstract: | 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. |
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