High-speed wind tunnel test of static aeroelastic load for large aspect-ratioand high flexible wing of civil aircraft

NI Zao; HUANG Yihuan; XIE Haijun

doi:10.7638/kqdlxxb-2024.0147

English Version Journal Login

您当前的位置：

首页 >

文章列表页 >

High-speed wind tunnel test of static aeroelastic load for large aspect-ratioand high flexible wing of civil aircraft

更新时间：2026-05-28

- High-speed wind tunnel test of static aeroelastic load for large aspect-ratioand high flexible wing of civil aircraft
- Vol. 43, Issue 6, Pages: 35-44(2025)
- 作者机构：
  
  中国商飞上海飞机设计研究院,上海,201210
- 作者简介：
- 基金信息：
- DOI：10.7638/kqdlxxb-2024.0147
  CLC： V211.74
- Published：2025
- 稿件说明：
移动端阅览
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.

关键词

Keywords

references

CHEN D W, YANG G W. Static aeroelastic analysis of a flying-wing using different models[J]. Chinese Journal of Theoretical and Applied Mechanics, 2009, 41(4): 469−479(in Chinese). doi: 10.6052/0459-1879-2009-4-2008-042

LIU F L, ZHAN H. High precision numerical simulation method for static aeroelastic analysis of wing[J]. Flight Dynamics, 2010, 28(4): 14−16(in Chinese). doi: 10.13645/j.cnki.f.d.2010.04.008

TAN L L, DU Y L. Aeroelastic load analysis of civil aircraft considering the large deformation[J]. Machine Design and Manufacturing Engineering, 2022, 51(10): 65−68(in Chinese). doi: 10.3969/j.issn.2095-509x.2022.10.013

GUO H T, CHEN D H, ZHANG C R, et al. Numerical applications on transonic static areoelasticity based on CFD/CSD method[J]. Acta Aerodynamica Sinica, 2018, 36(1): 12−16(in Chinese). doi: 10.7638/kqdlxxb-2015.0144

LIU Y, XU Y T, LYU J N. Aerodynamic analysis based on nonlinear aeroelastic large deformation for large aspect ratio wing[J]. Physics of Gases, 2020, 5(6): 39−44(in Chinese). doi: 10.19527/j.cnki.2096-1642.0811

FRENCH M. An application of structural optimization in wind tunnel model design[C]//31st Structures, Structural Dynamics and Materials Conference, Long Beach, CA, USA. AIAA, 1990: AIAA1990-956. doi: 10.2514/6.1990-956

FRENCH M, EASTEP F E. Aeroelastic model design using parameter identification[J]. Journal of Aircraft, 1996, 33(1): 198−202. doi: 10.2514/3.46922

YANG X M, LIU N, GUO C P, et al. A survey of aeroelastic wind tunnel test techonlogy of flight vehicles[J]. Acta Aerodynamica Sinica, 2018, 36(6): 995−1008(in Chinese). doi: 10.7638/kqdlxxb-2018.0039

HEEG J, SPAIN V, FLORANCE J, et al. Experimental results from the active aeroelastic wing wind tunnel test program[C]// 46th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference, Austin, Texas. AIAA, 2005: AIAA2005-2234. doi: 10.2514/6.2005-2234

ANDERSEN G, FORSTER E, KOLONAY R, et al. Multiple control surface utilization in active aeroelastic wing technology[J]. Journal of Aircraft, 1997, 34(4): 552−557. doi: 10.2514/2.2208

QIAN W, ZHANG G J, LIU Z K. Design, manufacture and low speed wind tunnel test of a high aspect ratio wing static aeroelastic model[J]. Journal of Experiments in Fluid Mechanics, 2013, 27(3): 93−97(in Chinese). doi: 10.3969/j.issn.1672-9897.2013.03.018

YANG X W, YU L, LV B B, et al. Experiment on static aeroelastic in high speed wind tunnel[J]. Acta Aerodynamica Sinica, 2015, 33(5): 667−672(in Chinese). doi: 10.7638/kqdlxxb-2014.0018

GUO H T, CHEN D H, LYU B B, et al. Wind tunnel test on transonic static areoelasticity of high-aspect-ratio wing[J]. Acta Aerodynamica Sinica, 2017, 35(6): 841−845(in Chinese). doi: 10.7638/kqdlxxb-2015.0075

ZHANG J G, SUN R J, JIN X. Test and study of static aeroelastic effects on wing's aerodynamic load[J]. Chinese Journal of Applied Mechanics, 2017, 34(3): 570−575,616(in Chinese). doi: 10.11776/cjam.34.03.B042

General Armaments Department of the People's Libe ration Army specification for wind tunnel strain gage balance: GJB 2244A—2011[S].

Views

下载量

CSCD

Alert me when the article has been cited

提交

Tools

Publicity Resources

Numerical and experimental study on flutter characteristics of a wing with drag rudder

Research on rolling instability of typical high-speed aircraft

Study on the wind load of low-rise buildings under typical mountainous terrain and the interference effects of surrounding buildings

Research on wind-induced interference effect of adjacent super tall buildings based on two-aeroelastic-model wind tunnel test

Wind load and wind-induced response of hybrid wind turbine towers

Related Author

LI Yongchang

HAN Yizhe

DAI Yuting

YANG Chao

CONG Rongfei

ZHAO Zhongliang

YE Youda

MA Shang

Related Institution

Hangzhou International Innovation Institute, Beihang University, Hangzhou

Tianmushan Laboratory, Hangzhou

School of Aeronautic Science and Engineering, Beihang University, Beijing

Beijing Aerodynamic Science Research Center, Beijing

High Speed Aerodynamics Institute of China Aerodynamics Research and Development Center, Mianyang

AI问答

⁰