Study on interaction between wing tip vortex and flat tail tip vortex
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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。尾涡的近场特性主要决定了着陆阶段飞机的尾涡强度。本文以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的流动显示实验。研究结果表明：平尾涡围绕翼尖涡旋转，不同流向站位的旋转角速度存在差异。通过分析对比模拟结果发现：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的相似性。Abstract: 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.
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Key words:
- wingtip vortex /
- rotation angle /
- water wind tunnel /
- numerical simulation
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图 6 翼尖涡与平尾涡位置关系分析
Figure 6. The positional relationship between wingtip vortex and horizontal tail vortex
图 7 不同流向位置的翼尖涡与平尾涡的位置关系
Figure 7. The positional relationship between the wingtip vortex and horizontal tail vortex in different profiles along flow direction
图 9 翼尖涡与平尾涡随流向的角速度变化趋势
Figure 9. The angular velocity of wingtip vortex and horizontal tail vortex along flow direction
图 14 飞行高度5 m与60 m状态下距翼尖不同位置处的涡量图
Figure 14. Vorticity profiles of different positions along flow direction for flying height 5 m and height 60 m
图 15 实验结果与数值模拟结果对比
Figure 15. The comparison between the experimental results and the numerical simulation results
表 1 模型主要参数
Table 1. Parameters of the model
参数 数值 翼展b/m 0.5 展弦比 8 升力系数（α=6°） 0.85 实验来流速度u/（m·s−1） 0.5 雷诺数 3.63×104 
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表 2 3种网格的升阻力系数
Table 2. The lift and drag coefficient of three grids
8M 20M 32M CL 0.8798 0.8799 0.8801 CD 0.0534 0.0529 0.0531 ΔCL −0.03% −0.02% − ΔCD 0.56% −0.38% −
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