翼尖链翼组合式无人机气动特性研究

王涵; 许晓平; 王贵晨; 李云龙

doi:10.7638/kqdlxxb-2024.0212

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翼尖链翼组合式无人机气动特性研究

研究论文 | 更新时间：2026-05-28

- 翼尖链翼组合式无人机气动特性研究
- Aerodynamic characteristics of combined wing-tip link UAV
- 空气动力学学报 2026年44卷第1期页码：59-75
- 作者机构：
  
  1. 西北工业大学航空学院,西安,710072
  2. 飞行器基础布局全国重点实验室,西安,710072
- 作者简介：
  
  王涵（2001—），男，重庆梁平人，硕士研究生，研究方向：飞行器气动布局设计与分析. E-mail：wanghan123@mail.nwpu.edu.cn
  许晓平*，副教授，研究方向：飞行器气动布局设计与分析. E-mail：xuran@nwpu.edu.cn
- 基金信息：
  
  国防基金（2021-JCJQ-JJ-0790）
- DOI：10.7638/kqdlxxb-2024.0212
  中图分类号： V279
- 纸质出版：2026
- 稿件说明：
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王涵, 许晓平, 王贵晨, 等. 翼尖链翼组合式无人机气动特性研究[J]. 空气动力学学报, 2026, 44(1): 59−75.

Wang Han, Xu Xiaoping, Wang Guichen, et al. Aerodynamic characteristics of combined wing-tip link UAV[J]. 2026, 44(1): 59-75.
王涵, 许晓平, 王贵晨, 等. 翼尖链翼组合式无人机气动特性研究[J]. 空气动力学学报, 2026, 44(1): 59−75. DOI： 10.7638/kqdlxxb-2024.0212

Wang Han, Xu Xiaoping, Wang Guichen, et al. Aerodynamic characteristics of combined wing-tip link UAV[J]. 2026, 44(1): 59-75. DOI： 10.7638/kqdlxxb-2024.0212.

摘要

为深入分析翼尖连接对组合式无人机气动特性的影响，本文建立了基于多面体网格的组合式无人机高保真数值模拟方法，并采用三维低雷诺数FX63-137平直机翼算例验证了计算方法的准确性。在雷诺数（1.5～2.0）×10

条件下，采用理论分析和数值模拟相结合的方式，系统研究了组合体与单体单元的升、阻力系数及升阻比变化特性，在此基础上推导建立了组合体气动特性随单体数量变化预测模型。研究结果表明，通过翼尖连接的方式可以显著提升组合式无人机的最大升阻比，如2机组合体相比单机的最大升阻比提升率可达约29.85%，其机理在于：翼尖连接可以显著增加组合式无人机的展弦比，使机翼升力分布更趋近于理想分布，同时消除了中部单元的翼尖涡干扰，减小了诱导阻力。但随着单体数量的增加，这种增升效应逐渐降低，同迎角下单体数量从9机增加到10机的最大升阻比提升率衰减至约1.84%，主要由于单体数量增加带来的气动力增量有限，对参考面积逐渐增大的组合体而言效果趋于弱化。此外，当单体飞机处于组合式无人机不同位置时，其气动特性会发生显著变化。具体而言，位于两侧的飞机气动特性提升效果仅为位于中部飞机的50%左右。经过进一步验证，本文推导建立的预测模型对不同构型的无人机组合体气动特性预测均具有较好的准确性和适用性，升、阻力系数的误差均在2%以内。

Abstract

To thoroughly analyze the impact of wingtip connection on the aerodynamic characteristics of composite drones

this study establishes a high-fidelity numerical simulation method based on polyhedral meshes. The accuracy of the computational approach was validated using a three-dimensional low-Reynolds-number FX63-137 straight wing case. Within the Reynolds number range of 1.5×10

to 2.0×10

a combined strategy of theoretical analysis and numerical simulation w

as employed to systematically investigate variations in the lift coefficient

drag coefficient

and lift-to-drag ratio of both the composite as a whole and its individual units. Based on the findings

a predictive model was developed to characterize how the aerodynamic performance of the formation varies with the number of units. The results indicate that wingtip connection can significantly enhance the maximum lift-to-drag ratio of composite drones. For instance

a two-unit composite achieves an improvement of approximately 29.85% compared to a single unit. This enhancement is attributed to a notable increase in the aspect ratio of the composite

leading to a lift distribution closer to the ideal pattern. Additionally

wingtip connection eliminates tip vortex interference from central units and reduces induced drag. However

as the number of units increases

this beneficial effect gradually diminishes. For example

when the number of units increases from 9 to 10

the improvement in the maximum lift-to-drag ratio at the same angle of attack decreases to about 1.84%. This attenuation occurs because the incremental aerodynamic benefit from adding more units becomes limited and is increasingly diluted relative to the growing reference area of the formation. Moreover

the aerodynamic characteristics of an individual aircraft vary significantly depending on its position within the composite drone. Specifically

the enhancement in aerodynamic performance for the aircraft positioned on both sides is only approximately 50% of that achieved by the central aircraft. Further validation confirms that the proposed predictive model demonstrates high accuracy and applicability in estimating the aerodynamic characteristics of formation drones across various configurations

with errors in both lift and drag coefficients within 2%.

关键词

Keywords

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