高分辨率激波/边界层干扰时间演化过程分析  

Time evolution process of high resolution shock wave/turbulent boundary layer interaction

作　　者：陆小革 易仕和[1] 何霖[1] 全鹏程[1] 冈敦殿[1] LU Xiaoge;YI Shihe;HE Lin;QUAN Pengcheng;GANG Dundian(College of Aerospace Science and Engineering,National University of Defense Technology,Changsha 410073,China)

机构地区：[1]国防科技大学空天科学学院,长沙410073

出　　处：《航空学报》2022年第1期124-135,共12页Acta Aeronautica et Astronautica Sinica

基　　金：国家重点研发计划(2019YFA0405300);国家重大科研仪器研制项目(11527802);国家自然科学基金重大研究计划(91752102,11832018)。

摘　　要：采用基于纳米示踪的平面激光散射(NPLS)技术,探索了流场超高帧频成像测试研究的试验系统,主要解决了多个单脉冲激光器并联后的稳定性和合束、阵列CCD相机的整体设计和布局以及测试系统的同步精确控制等问题,通过对系统的时序和分系统调试,实现了测试系统的精确控制。基于此系统,在单位雷诺数为6.30×10^(6)/m的条件下,在马赫数为3.4的超声速低噪声风洞中开展了θ=20°激波发生器入射激波与来流壁面湍流边界层干扰相关试验研究。在试验条件下获得了序列连续时间相关的激波与湍流边界层干扰的瞬态流场精细结构图像,并分析了其流场结构的时空演化特性。In this paper,a test system based on the Nano-tracer Planar Laser Scattering(NPLS)technique for studying time evolution of unsteady flow structures is developed to solve the problems of stability and beam combination after parallel connection of multiple monopulse lasers,the overall design and layout of array CCD cameras,and the synchronous and accurate control of the test system.Based on this system,the experimental study on the interactions between the incident shock wave ofθ=20°shock generator and the turbulent boundary layer of the incoming wall was performed.The experiments are performed in a Mach number 3.4 supersonic low-noise wind tunnel at the unit Reynolds number of 6.30×10^(6)/m.For the first time,eight frames of temporal-correlated fine structure images of transient flow field with shock wave/turbulent boundary layer interaction are obtained under the experimental conditions,and the spatio-temporal evolution characteristics of the flow structure are analyzed.

关 键 词：超声速边界层 STBLI 超高帧频 时空演化特性 NPLS 低噪声风洞 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程]