飞机尾涡对的三维失稳快速模拟方法

徐梓铭; 李栋; 蔡金延; 李沛繁

doi:10.7638/kqdlxxb-2023.0101

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飞机尾涡对的三维失稳快速模拟方法

研究专栏——大型飞机尾涡演化的预测、测量及控制 | 更新时间：2026-05-28

- 飞机尾涡对的三维失稳快速模拟方法
- Fast simulation method for three dimensional instability of an aircraft wake vortex pair
- 空气动力学学报 2025年43卷第1期页码：95-104
- 作者机构：
  
  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,绵阳,621000
- 作者简介：
  
  徐梓铭（1998—），陕西延安人，博士研究生，研究方向：飞机尾涡演化. E-mail：xzm199826@mail.nwpu.edu.cn
  李栋*，教授，研究方向：空气动力学，飞行器设计. E-mail：ldgh@nwpu.edu.cn
- 基金信息：
  
  国家自然科学基金（U1733203）
- DOI：10.7638/kqdlxxb-2023.0101
  中图分类号： V211.3
- 纸质出版：2025
- 稿件说明：
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徐梓铭, 李栋, 蔡金延, 等. 飞机尾涡对的三维失稳快速模拟方法[J]. 空气动力学学报, 2025, 43(1): 95−104.

XU Ziming, LI Dong, CAI Jinyan, et al. Fast simulation method for three dimensional instability of an aircraft wake vortex pair[J]. 2025, 43(1): 95-104.
徐梓铭, 李栋, 蔡金延, 等. 飞机尾涡对的三维失稳快速模拟方法[J]. 空气动力学学报, 2025, 43(1): 95−104. DOI： 10.7638/kqdlxxb-2023.0101

XU Ziming, LI Dong, CAI Jinyan, et al. Fast simulation method for three dimensional instability of an aircraft wake vortex pair[J]. 2025, 43(1): 95-104. DOI： 10.7638/kqdlxxb-2023.0101.

摘要

飞机尾流是制约机场飞行间隔缩短的重要因素之一，然而当前的尾流演化数值模拟和经验模型均无法兼顾尾流演化的时效性和准确性，不利于管制机场尾流间隔。考虑到飞机尾流由飞机尾涡对主导，而动力学失稳又是飞机尾涡耗散的主要机制，本文提出基于曲率修正涡丝法的飞机尾涡对失稳快速模拟方法。通过三次样条插值得到涡段中点坐标，将直涡段处理为弯曲涡段，同时考虑涡段对自身控制点的诱导作用，实现涡丝法诱导速度的曲率修正。另外，给出了涡丝法模拟飞机尾涡对周期条件的处理方法，大幅提升了涡丝法模拟飞机尾涡失稳的计算精度。数值实验结果表明，考虑曲率修正的涡丝法能够以较低的计算成本实现快速预测尾涡对长波失稳，并且失稳增长率、涡丝倾角均与理论值吻合良好。在施加不同强度的湍流扰动后，本文方法模拟得到的涡对快速耗散时间与理论值吻合较好，尤其对于中弱强度的湍流扰动，本文方法预测结果更为准确。

Abstract

Aircraft wake is one of the important factors restricting the flight interval between two aircraft in the airport. However

current numerical simulation methods and empirical models cannot take the timeliness and accuracy of the wake evolution at the same time

which is not conducive to the control of airport wake interval. Considering that the aircraft wake is dominated by aircraft wake vortex pairs

whose dynamic instability is the main mechanism of aircraft wake vortex dissipation

this study proposes a fast simulation method for aircraft wake vortex pair instability based on the curvature corrected vortex filament method. Through cubic spline interpolation

the midpoint coordinates of vortex segments are extracted to treat the straight vortex segments as curved ones

and the induced effects of vortex segments on their own control points are also considered

thus the curvature correction of induced velocity in the vortex filament method is realized. The treatment of period conditions in simulating the vortex pair is given

which greatly improves the accuracy of aircraft wake vortex instability prediction. The results of numerical experiments show that

the curvature corrected vortex filament method can make a fast prediction of the long wave instability of aircraft wake vortex pairs at a low cost

and the instability growth rate and inclination angle of the vortex filaments are in good agreement with the theoretical values. When turbulence with different intensities is applied

the dissipation time of vortex pairs simulated by the present method is in good agreement with the theoretical prediction. Particularly

the present method is more accurate for turbulence with moderate or weak intensity.

关键词

Keywords

references

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