机翼翼尖涡与平尾翼尖涡的相互作用研究  

Study on interaction between wing tip vortex and flat tail tip vortex

作　　者：张泽宇[1] 李栋[1] 周金鑫 梁勇[2] 耿子海[2] ZHANG Zeyu;LI Dong;ZHOU Jinxin;LIANG Yong;GENG Zihai(School of Aeronautics,Northwestern Polytechnical University,Xi’an 710072,China;Low Speed Aerodynamics Institute,China Aerodynamics Research and Development Center,Mianyang 621000,China)

机构地区：[1]西北工业大学航空学院,西安710072 [2]中国空气动力研究与发展中心低速空气动力研究所,绵阳621000

出　　处：《实验流体力学》2024年第5期29-36,共8页Journal of Experiments in Fluid Mechanics

基　　金：民航联合研究基金(U173320010)。

摘　　要：飞机尾涡的发展与同跑道降落后机的飞行安全及机场起降效率密切相关。尾涡近场特性主要决定了着陆阶段飞机的尾涡强度。以A320飞机简化缩比模型为研究对象,在1 m×1 m低速水洞中开展了尾涡近场形态流动显示实验。研究结果表明:平尾涡在拖出过程中围绕翼尖涡旋转,不同流向站位的旋转角速度存在差异。对比模拟结果发现:平尾涡绕翼尖涡的旋转角速度与实验结果基本吻合,说明不同雷诺数下涡对发展在相对位置旋转角速度特性方面具有一定相似性。The development of the wingtip vortex is an important factor for the flight safety and airport efficiency of the aircraft landing on the runway.The near-field characteristics of the wingtip vortex mainly determine the vorticity of the vortex in the landing phase.In this paper,a simplified model of A320 is used as the object to observe the near-field configuration of the wingtip vortex in a low-speed tunnel of 1 m×1 m.It is found that the horizontal tail vortex rotates around the wingtip vortex,and the rotational angular velocity in different flow stations is different.By comparing the simulation results,it is found that the rotational angular velocity of the horizontal tail vortex around the wingtip vortex is basically consistent with the experimental results,indicating that the development of the wake vortex under different Reynolds numbers has certain similarity in the characteristics of the rotational angular velocity between two vortices.

关 键 词：翼尖涡 旋转角速度 平尾涡 数值模拟 低速水洞 

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]