泡沫碳表面对高超声速边界层稳定性影响  

Stabilization effects of carbon foam surface on hypersonic boundary layers

作　　者：王蔚彰 赵瑞[1] 桂裕腾 吴杰 涂国华[3] WANG Weizhang;ZHAO Rui;GUI Yuteng;WU Jie;TU Guohua(School of Aerospace Engineering,Beijing Institute of Technology,Beijing 100081,China;School of Aeronautics and Astronautics,Huazhong University of Science and Technology,Wuhan 430074,China;State Key Laboratory of Aerodynamics,China Aerodynamics Research and Development Center,Mianyang 621000,China)

机构地区：[1]北京理工大学宇航学院,北京100081 [2]华中科技大学航空航天学院,武汉430074 [3]中国空气动力研究与发展中心空气动力学国家重点试验室,绵阳621000

出　　处：《北京航空航天大学学报》2023年第10期2741-2749,共9页Journal of Beijing University of Aeronautics and Astronautics

摘　　要：高超声速边界层转捩会使壁面摩阻和热流显著增加,严重影响飞行器的性能。微孔隙表面在不明显改变平均流场的同时,能够有效抑制边界层转捩,具有较大的应用潜力。在马赫数为6的Ludwieg管风洞中研究泡沫碳孔隙材料对尖锥边界层中不稳定波的影响规律,试验结果表明:尖锥边界层存在明显的第2模态波,其特征频率随着流向位置增加而减小。相比于光滑表面,泡沫碳表面使不同流向位置上的第2模态波增长率均有明显下降,至少延长第2模态传播区域21.6%。此外,采用阻抗管测量泡沫碳表面的声学特性获取阻抗模型系数,并结合线性稳定性理论预测了泡沫碳表面扰动模态增长率,理论结果与试验结果变化趋势相同。Hypersonic boundary-layer transition generates a significant increase in skin friction and heat flux,which leads to severe restrictions on the performance of hypersonic vehicles.Micropore surfaces have a significant deal of potential for application since they can successfully prevent boundary layer transition without clearly altering the average flow field.The effects of carbon foam material on unstable modes in hypersonic boundary-layer are studied in Mach 6 Ludwieg wind tunnel,the experimental results indicate that there exists an obvious second mode wave in the boundary layer,and its characteristic frequency decreases downstream.The carbon foam surface,when compared to a smooth surface,at various streamwise positions retards the formation of the second mode wave and increases the second mode propagation area by at least 21.6%.In addition,the impedance tube is used to measure the acoustic characteristics of the carbon foam surface to obtain impedance model coefficients.The linear stability theory is used to predict the growth rate of disturbance mode on the carbon foam surface,and the theoretical results have the same trend as the experimental results.

关 键 词：边界层稳定性 微孔隙表面 高超声速 风洞试验 线性稳定性理论 

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] O354.4[理学—流体力学]