民用飞机大展弦比大柔性机翼高速静气动弹性载荷风洞试验

尼早; 黄一桓; 谢海军

doi:10.7638/kqdlxxb-2024.0147

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民用飞机大展弦比大柔性机翼高速静气动弹性载荷风洞试验

研究论文 | 更新时间：2026-05-28

- 民用飞机大展弦比大柔性机翼高速静气动弹性载荷风洞试验
- High-speed wind tunnel test of static aeroelastic load for large aspect-ratioand high flexible wing of civil aircraft
- 空气动力学学报 2025年43卷第6期页码：35-44
- 作者机构：
  
  中国商飞上海飞机设计研究院,上海,201210
- 作者简介：
  
  尼早*（1985—），男，河南郑州人，研究员，研究方向：飞机载荷与气动弹性. E-mail：nizao@comac.cc
- 基金信息：
- DOI：10.7638/kqdlxxb-2024.0147
  中图分类号： V211.74
- 纸质出版：2025
- 稿件说明：
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尼早, 黄一桓, 谢海军. 民用飞机大展弦比大柔性机翼高速静气动弹性载荷风洞试验[J]. 空气动力学学报, 2025, 43(6): 35−44.

NI Zao, HUANG Yihuan, XIE Haijun. High-speed wind tunnel test of static aeroelastic load for large aspect-ratioand high flexible wing of civil aircraft[J]. 2025, 43(6): 35-44.
尼早, 黄一桓, 谢海军. 民用飞机大展弦比大柔性机翼高速静气动弹性载荷风洞试验[J]. 空气动力学学报, 2025, 43(6): 35−44. DOI： 10.7638/kqdlxxb-2024.0147

NI Zao, HUANG Yihuan, XIE Haijun. High-speed wind tunnel test of static aeroelastic load for large aspect-ratioand high flexible wing of civil aircraft[J]. 2025, 43(6): 35-44. DOI： 10.7638/kqdlxxb-2024.0147.

摘要

针对大展弦比大柔性机翼高速静气动弹性问题，通过开展大展弦比大柔性机翼高速静气动弹性载荷风洞试验，采用机翼翼根测力、模型变形视频测量等多种测量手段，研究了静气动弹性效应对机翼气动特性及载荷结果的影响。试验结果表明，固定马赫数下，迎角为正时，弹性模型的升力和阻力系数均小于刚性模型；固定迎角下，在不同马赫数范围内，弹性模型的升力、阻力系数和升力线斜率均小于刚性模型。在迎角0°～6°的范围内，翼根弯矩弹刚比小于翼根剪力弹刚比，证实了大展弦比大柔性机翼的静气动弹性效应可以在机翼翼根剪力不变的情况下有效降低机翼翼根弯矩。流场显示结果表明，机翼翼尖最大变形超过200 mm。机翼外侧受弹性变形影响产生了负扭转，减小了当地迎角，从而降低了翼根的剪力、弯矩和扭矩。本研究明确了静气动弹性效应对机翼载荷的重要影响，为大展弦比大柔性机翼载荷设计提供了设计依据。

Abstract

This study investigates the static aeroelastic characteristics of large-aspect-ratio highly flexible wings under high-speed conditions through wind tunnel testing. Multiple measurement techniques were employed

including wing-root force measurement and videogrammetric model deformation

to investigate the effects of static aeroelasticity on aerodynamic characteristics and load distributions. The results demonstrated that at fixed Mach numbers with positive angles of attack

the elastic model exhibited lower lift and drag coefficients compared to the rigid model. Furthermore

under constant angles of attack across different Mach number ranges

the elastic model demonstrated reduced lift coefficients

drag coefficients

and lift-curve slopes relative to rigid model. Within the range of 0 °～6 ° angle of attack

the elastic stiffness ratio of the wing bending moment was lower than that of the wing shear. This confirms that the static aeroelastic effects of high aspect ratio flexible wings can effectively reduce the wing bending moment while maintaining constant wing shear. The maximum deformation of the wing tip exceeded 200 mm by flow field visualization. Negative torsion occurred near the wing tip due to elastic deformation

reducing the local angle of attack

thereby reducing the shear force

bending moment

and torque at the wing root. This study provides the load design basis for large aspect-ratio and high flexible wings.

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references

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