攻角和单位雷诺数对HyTRV升力体高超声速边界层转捩影响的实验研究  

Experimental study on the influence of angle of attack and unit Reynolds number on the transition of the hypersonic boundary layer of the HyTRV lifting body

作　　者：张成键 吴杰 陈坚强 ZHANG ChengJian;WU Jie;CHEN JianQiang(School of Aerospace Engineering,Huazhong University of Science and Technology,Wuhan 430074,China;State Key Laboratory of Aerodynamics,Mianyang 621000,China)

机构地区：[1]华中科技大学航空航天学院,武汉430074 [2]空天飞行空气动力科学与技术全国重点实验室,绵阳621000

出　　处：《中国科学：物理学、力学、天文学》2024年第10期97-111,共15页Scientia Sinica Physica,Mechanica & Astronomica

基　　金：国家自然科学基金(编号:9052301)资助项目。

摘　　要：为了获得更高的升阻比,真实飞行条件下的飞行器一般是带有攻角飞行,攻角变化会导致飞行器表面压力梯度的变化,进而对飞行器的边界层转捩产生重要影响.本文针对HyTRV高超声速飞行器升力体构型的模型,在马赫6 Ludwieg管风洞中采用高频压力传感器(PCB)和高速红外相机对不同攻角下的HyTRV模型边界层进行了实验测量,分析了HyTRV的腹部流向涡区、腰部横流区和肩部流向涡区的不稳定性特征.实验结果表明,腹部流向涡区的转捩位置随着攻角增加而变化不大,主要是因为随着攻角的增加该处的转捩机理发生了改变;HyTRV模型背风面处原本独立的转捩区在攻角增加的情况下发生了移动、融合扩张,导致腰部横流区和肩部流向涡区转捩的主导模态随着攻角的增加发生了改变,腰部横流区的主导模态由横流的二次失稳模态变为第二模态,肩部流向涡区的主导模态由流向涡模态变为横流的二次失稳模态.To achieve a higher lift-to-drag ratio,aircraft under real flight conditions typically fly with an angle of attack.Changes in angle of attack cause variations in surface pressure gradients,significantly affecting the boundary layer transition of the aircraft.This study focused on the model of the HyTRV hypersonic flying body configuration.Experimental measurements of the boundary layer of the HyTRV model at different angles of attack were conducted in a Mach 6 Ludwieg tube wind tunnel using high-frequency pressure sensors(PCB)and high-speed infrared cameras.The study analyzed the instability characteristics of the flow vortex region at the abdomen,the transverse flow region at the waist,and the flow vortex region at the shoulders of the HyTRV.The experimental results indicate that the transition position of the flow vortex region at the abdomen changes little with increasing angle of attack.This stability is primarily due to alterations in the transition mechanism at that location as the angle of attack increases.On the windward side of the HyTRV model,the originally independent transition zones undergo movement,merging,and expansion with increasing angle of attack.This phenomenon causes changes in the dominant transition modes of the transverse flow region at the waist and the flow vortex region at the shoulders.Specifically,the dominant mode in the transverse flow region at the waist shifts from the secondary instability mode of transverse flow to the second mode,while the dominant mode in the flow vortex region at the shoulders shifts from the flow vortex mode to the secondary instability mode of transverse flow.

关 键 词：高超声速 边界层稳定性 HyTRV升力体 不同攻角 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程] V411