不同入射激波条件下激波与湍流边界层干扰的实验研究  

Experimental study on shock and turbulent boundary layer interactions under different incident shock waves

作　　者：陆小革 易仕和[1] 牛海波 何霖[1] 冈敦殿[1] LU XiaoGe;YI ShiHe;NIU HaiBo;HE Lin;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：《中国科学：物理学、力学、天文学》2020年第10期57-68,共12页Scientia Sinica Physica,Mechanica & Astronomica

基　　金：国家重点研发计划(编号:2019YFA0405300,2016YFA0401200);国家重大科研仪器研制项目(编号:11527802);国家自然科学基金重大研究计划(编号:91752102,11832018)资助项目。

摘　　要：本文在Ma=3.4超声速低噪声风洞中开展了不同入射激波条件下激波与来流壁面湍流边界层干扰的相关实验研究,得到了不同入射激波条件下的精细流场结构、壁面压力、壁面温度分布以及他们之间的相互关系.利用基于纳米示踪的平面激光散射技术(NPLS)在单位雷诺数6.30×106m-1条件下获得了激波与湍流边界层干扰典型流场精细的瞬态流动结构图像,并对瞬态流动图像进行统计分析,得到的诱导激波振荡位置满足正态分布.同时利用大气数据系统得到了不同入射激波条件下干扰区的壁面压力分布,以及不同入射激波强度下分离区流动结构与壁面压力变化的关系.利用温敏漆(TSP)技术,得到不同入射激波条件下干扰区模型壁面温度分布,分析了激波与湍流边界层干扰过程中出现G?rtler涡引起的条带结构与入射激波强度的关系.In this paper,the interactions between shock wave and the turbulent boundary layer of an incoming wall were experimentally studied.The experiments were performed in a Mach 3.4 supersonic low-noise wind tunnel at the unit Reynolds number of 6.30×106 m-1.Under different incident shock wave conditions,fine flow field structure,wall pressure,and wall temperature distribution were determined.Relationship was also analyzed.Instantaneous fine structures of typical flow fields with shock wave and turbulent boundary layer interactions were investigated using the nano-tracer planar laser scattering technique,and the transient flow images were analyzed statistically.The oscillation position of the induced shock wave satisfies a normal distribution.Simultaneously,the wall pressure distribution under different incident shockwave conditions of the interaction region was determined using the flush air data sensing system,and the relationship between flow the structure of the separation region and the wall pressure distribution with different incident shock wave intensities is analyzed.Using a temperature sensitive paint technology,the wall temperature distribution under different incident shockwave conditions of the interaction region model was determined.Also,the relationship between the strip structure caused by G?rtler vortices and the incident shock wave intensity in the shockwave/turbulent boundary layer interaction was analyzed.

关 键 词：超声速边界层 激波与湍流边界层干扰(SWTBLI) 纳米示踪的平面激光散射技术(NPLS) 温敏漆(TSP) 

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] V411