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, 2021, 39(s): 1−10. doi: 10.7638/kqdlxxb-2023.0101
引用本文: 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, 2021, 39(s): 1−10. doi: 10.7638/kqdlxxb-2023.0101
XU Z M, LI D, CAI J Y, et al. Fast simulation method for three dimensional instability of an aircraft wake vortex pair[J]. Acta Aerodynamica Sinica, 2021, 39(s): 1−10. doi: 10.7638/kqdlxxb-2023.0101
Citation: XU Z M, LI D, CAI J Y, et al. Fast simulation method for three dimensional instability of an aircraft wake vortex pair[J]. Acta Aerodynamica Sinica, 2021, 39(s): 1−10. doi: 10.7638/kqdlxxb-2023.0101

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

  • 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.

     

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