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

  • 摘要: 静气动弹性问题对飞机的气动设计和载荷设计研究具有重要意义,目前数值计算和风洞试验是研究静气弹问题的主要手段。本文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,对风洞试验方法进行了系统研究,并在此基础上进一步研究了静气动弹性效应对机翼载荷的影响,证实了大展弦比大柔性机翼的静气动弹性效应具有降低机翼载荷的效果。试验结果表明,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。本文的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: The study of static aeroelasticity is of significant importance for the aerodynamic and load design of aircraft. At present, numerical computation and wind tunnel testing are the principal methods for studying static aeroelastic problems. In this work, the wind tunnel test method for high-speed static aeroelastic load of civil aircraft with large aspect-ratio and high flexible wings is systematically investigated. On this basis, the influence of static aeroelastic effect on the wing load is thoroughly studied. Experiments confirm that the static aeroelastic effects of a high flexible wing with large aspect ratio can produce a load reduction effect. The experimental results show that within the range of 0 °~6 ° angle of attack, the wing bending moment elastic stiffness ratio is smaller than the wing shear elastic stiffness ratio, confirming that the static aeroelastic effect of a high aspect ratio flexible wing can effectively reduce the wing bending moment while maintaining constant wing shear. The maximum deformation of the wing tip exceeds 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. The present results provide the load design basis for large aspect-ratio and high flexible wings.

     

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