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Planform and Flexibility on Lift Characteristics for Flow over Low-Aspect Ratio Wings

机译：低纵横比机翼流动的升力特性的平面形式和灵活性

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摘要

Force measurement and surface oil flow visualization were carried out in wind tunnel to investigate the effects of wing's planform and flexibility on aerodynamics for flow over low-aspect ratio wings. It is found that the empirical formulas proposed by Polhamus can present remarkably accurate predictions before stall for both rigid and flexible wings. The spiral vortex is responsible for rigid and flexible wing abrupt drop of lift coefficient after stall when the sweep angle is below 35°. The maximum lift coefficient and the stall angle for flexible wings are smaller than those for rigid ones when the sweep angle is below 40°, and the wing flexibility nearly does not influence the aerodynamics as the sweep angle is beyond 40°. Moreover, lift coefficient curves exist hysteresis loop in the following range of sweep angle: 10°-35° for the flexible wings and 5°-50° for the rigid wings. It can be deduced from oil visualization experiment that the sudden disappearance of spiral vortex flow structure may be responsible for the hysteresis.
机译：在风洞中进行力测量和表面油流可视化，以研究机翼的平面形状和柔性对低纵横比机翼流动的空气动力学的影响。结果发现，Polhamus提出的经验公式可以为刚性和柔性机翼在失速之前提供非常准确的预测。当后掠角低于35°时，螺旋涡旋导致失速后刚性和柔性机翼的升力系数突然下降。当后掠角低于40°时，挠性机翼的最大升力系数和失速角小于刚性机翼，并且当后掠角超过40°时，机翼挠性几乎不影响空气动力学。此外，升力系数曲线在以下后掠角范围内存在磁滞回线：柔性机翼为10°-35°，刚性机翼为5°-50°。从油的可视化实验可以推论出螺旋涡流结构的突然消失可能是造成滞后的原因。

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  • 来源
    《Journal of aerospace engineering》 |2010年第1期|p.55-61|共7页
  • 作者

    L. X. Zuo; J. J. Wang;

  • 作者单位

    Institute of Fluid Mechanics, Beijing Univ.of Aeronautics and Astronautics, Beijing 100083, China;

    Professor, Institute of Fluid Mechanics, Beijing Univ. of Aeronautics and Astronautics, Beijing 100083, China;

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