壁温对高超声速裙锥边界层感受性的影响规律  

Influence of wall temperature on receptivity of hypersonic flare cone boundary layer

作　　者：张定金 雷娟棉 赵瑞[1] Dingjin ZHANG;Juanmian LEI;Rui ZHAO(School of Aerospace Engineering,Beijing Institute of Technology,Beijing 100083,China)

机构地区：[1]北京理工大学宇航学院,北京100083

出　　处：《航空学报》2024年第24期150-166,共17页Acta Aeronautica et Astronautica Sinica

基　　金：国家自然科学基金(12272049)。

摘　　要：外界扰动进入边界层的感受性过程对转捩位置预测十分关键。结合直接数值模拟和线性稳定性分析方法,在马赫数为6的高超声速条件下研究了壁温对自由流高斯扰动激发裙锥边界层内扰动的感受性的影响。结果表明,自由流高斯扰动穿过裙锥头部激波后激发出快声波、熵波,其中快声波的幅值最大,并且快声波幅值随着壁温升高而增大。之后快声波先激发出裙锥边界层内快模态,进而通过模态转换机制激发出Mack第二模态。降低壁温会使第一模态趋于稳定,但会激发Mack第二模态。最后,从直接数值模拟结果中通过傅里叶变换获取了感受性系数随壁温变化的规律,结果表明感受性系数随壁温的升高而增大。The receptivity process of external disturbances entering the boundary layer is crucial for predicting the transition location.Employing a combination of direct numerical simulation and linear stability analysis methods,this study investigates the influence of wall temperature on the receptivity of freestream Gaussian disturbances exciting disturbances within the flare cone boundary layer at Mach number 6.The findings indicate that Gaussian disturbances after passing through the shockwave excite fast acoustic waves and entropy waves at the head of the cone,with the amplitude of the fast acoustic waves being maximized.Additionally,the amplitude of fast acoustic waves increases with the increase of the wall temperature.Subsequently,the fast acoustic waves initiate the fast modal behavior within the boundary layer,and then excite the Mack second mode through a modal transformation mechanism.Decreasing wall temperature stabilizes the first mode,but renders the Mack second mode more unstably.Finally,Fourier transforms applied to the results of direct numerical simulations reveal a pattern of variation of receptivity coefficients with wall temperature,indicating that receptivity coefficients increase with the rise of wall temperature.

关 键 词：感受性 高斯扰动 直接数值模拟 线性稳定性分析 高超声速边界层 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]