Investigation of design methodology for two-element airfoil of medium altitude and long endurance UAV

LI Jianhua; LI Feng; LI Maoqiang; YU Yueyang

doi:10.7638/kqdlxxb-2017.0130

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Investigation of design methodology for two-element airfoil of medium altitude and long endurance UAV

更新时间：2026-05-28

- Investigation of design methodology for two-element airfoil of medium altitude and long endurance UAV
- Vol. 37, Issue 5, Pages: 813-818(2019)
- 作者机构：
  
  中国航天空气动力技术研究院航天彩虹无人机股份有限公司,北京,100074
- 作者简介：
- 基金信息：
- DOI：10.7638/kqdlxxb-2017.0130
  CLC： V211.3
- Published：2019
- 稿件说明：
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李建华, 李锋, 李茂强, 于悦洋. 中空长航时无人机两段翼型设计研究[J]. 空气动力学学报, 2019, 37(5): 813-818.

LI Jianhua, LI Feng, LI Maoqiang, et al. Investigation of design methodology for two-element airfoil of medium altitude and long endurance UAV[J]. 2019, 37(5): 813-818.
李建华, 李锋, 李茂强, 于悦洋. 中空长航时无人机两段翼型设计研究[J]. 空气动力学学报, 2019, 37(5): 813-818. DOI： 10.7638/kqdlxxb-2017.0130.

LI Jianhua, LI Feng, LI Maoqiang, et al. Investigation of design methodology for two-element airfoil of medium altitude and long endurance UAV[J]. 2019, 37(5): 813-818. DOI： 10.7638/kqdlxxb-2017.0130.

摘要

中空长航时无人机存在高效巡航、短距起降以及抗变形等多性能要求，本文在原始飞机单段翼型的基础上，开展多约束条件下两段翼型设计方法研究和翼型设计。采用控制点加分段可控二次曲线方法构建两段翼型外形，并对生成外形的控制参数、缝道参数和转轴位置进行优化设计。分析结果表明：相比于常规直接切割法，本文采用的方法控制点和控制参数更多，对原始翼型适应性更好，生成的翼型压力分布更加合理；与原始翼型相比，新设计的两段翼型在续航因子、起飞升力和起飞升阻比方面得到大幅提升；同时襟翼大角度偏转还能起到阻力板作用，达到对巡航和起降多设计点综合设计要求。

Abstract

According to the design requirements related to high endurance factor

short take-off and landing

deforming resistance of MALE UAV

the investigation of the design methodology on multi-constraints two-element airfoil is conducted based upon the earlier studies on the one-element airfoil. In this paper

the geometry of the two-element airfoil is generated with the method of controllable conic curves accompanied with the control points

and the parameters of control curves

slot and spin axis position are optimized using Genetic Algorithms. The results indicate that

compared with the ellipse cutting method

the present method using more control parameters is more flexible to the earlier airfoil with more reasonable pressure distributions. Moreover

the endurance factor

take-off lift and lift-to-drag ratio of the designed slot airfoil are improved substantially. In addition

flaps with wide angle deflection play the role of deceleration during landing. The designed slot airfoil satisfies multiple demands and the present method is suitable for the MALE UAV design.

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Keywords

references

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