空气动力学学报2025，Vol.43Issue(6)：35-44,10.DOI:10.7638/kqdlxxb-2024.0147
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-ratio and high flexible wing of civil aircraft
尼早 1黄一桓 1谢海军1
作者信息
- 1. 中国商飞上海飞机设计研究院,上海 201210
- 折叠
摘要
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
静气动弹性/机翼载荷/风洞试验/大柔度机翼/大展弦比机翼Key words
static aeroelastic/wing load/wind tunnel test/large flexible wing/large aspect-ratio wing分类
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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):35-44,10.
