HyTRV升力体高超声速边界层稳定性实验  

Hypersonicboundarylayers xperiment of HyTRV lift body

作　　者：张成键 吕岱霖 朱畅 陈坚强 吴杰 ZHANG Chengjian;LYU Dailin;ZHU Chang;CHEN Jianqiang;WU Jie(School of Aerospace Engineering,Huazhong University of Science and Technology,Wuhann430074,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：《航空学报》2024年第22期112-125,共14页Acta Aeronautica et Astronautica Sinica

基　　金：国家自然科学基金(92052301)。

摘　　要：HyTRV升力体是高超声速下为研究三维复杂外形的边界层转捩问题而设计的一款具有真实飞行器特征的标模。目前针对于该标模的研究主要是基于理论分析和数值计算,缺乏实验数据的验证。为了给HyTRV升力体模型转捩理论验证、转捩模型构建以及转捩控制等提供风洞试验数据,在马赫数6 Ludwieg管风洞中采用高频压力传感器和高速红外相机对HyTRV升力体进行了边界层稳定性的实验测量,分析了HyTRV模型腹部流向涡区、腹部横流区、腰部横流区和肩部流向涡区的边界层不稳定性特征,重点对获取到明显不稳定波的腹部横流区进行了研究。实验结果显示:HyTRV模型的腹部流向涡区存在10~30 kHz的微弱低频不稳定波;腹部横流区测得了150~250 kHz的高频不稳定波,0°攻角下该不稳定波的传播速度为722.9 m/s,推测该不稳定波为横流扰动的高频二次失稳模态;腰部横流区和肩部流向涡区观察到了边界层转捩的过程,但并未发现明显的不稳定波特征。红外测量结果显示模型迎风面和背风面的转捩阵面与直接数值模拟结果吻合良好,且模型的迎风面观察到典型锯齿状条纹转捩阵列,与腹部横流区横流不稳定性主导失稳转捩的结论一致。The HyTRV lift body is a standard model designed for studying boundary layer transition issues in threedimensional complex geometry at hypersonic flow,with characteristics similar to those of a real aircraft.Currently,research on this model mainly relies on theoretical analysis and numerical calculations,lacking experimental data for validation.To provide wind tunnel test data for theoretical verification and control of boundary layer transition on the HyTRV lift body,we used high-frequency pressure sensors and high-speed infrared cameras to conduct experimental measurements of boundary layer stability in the Mach number 6 Ludwieg tube wind tunnel.The study analyzed the instability characteristics of the boundary layer in the flow separation region,the transverse flow region,the waist transverse flow region,and the shoulder flow separation region of the HyTRV model,with a focus on investigating instability waves in the transverse flow region of the model belly.The experimental results show that the vortex region of the Hy-TRV model belly exhibits weak low-frequency instability waves at 10-30 kHz,while high-frequency instability waves of 150-250 kHz were measured in the cross-flow region of the belly.At a 0°angle of attack,the propagation speed of this instability wave was determined to be 722.9 m/s,suggesting that this instability wave is a high-frequency unstable mode of the secondary crossflow instability.The process of boundary layer transition was observed in the waist crossflow region and the shoulder vortex region,with no obvious instability wave characteristics found.Infrared measurement results show good agreement between the model leading edge and trailing edge transition fronts and direct nu-merical simulation results.Additionally,typical sawtooth-like streaky transition arrays were observed on the model leading edge,consistent with the conclusion that cross-flow instability dominates unstable transition in the cross-flow region of the belly.

关 键 词：高超声速 边界层稳定性 HyTRV升力体 不稳定性实验 转捩 

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]