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首页> 外文期刊>Mathematical Problems in Engineering >Influence of Thickness Variation on the Flapping Performance of Symmetric NACA Airfoils in Plunging Motion
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Influence of Thickness Variation on the Flapping Performance of Symmetric NACA Airfoils in Plunging Motion

机译：插拔运动中厚度变化对对称式NACA机翼拍打性能的影响

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摘要

In order to investigate the impact of airfoil thickness on flapping performance, the unsteady flow fields of a family of airfoils from an NACA0002 airfoil to an NACA0020 airfoil in a pure plunging motion and a series of altered NACA0012 airfoils in a pure plunging motion were simulated using computational fluid dynamics techniques. The "class function/shape function transformation" parametric method was employed to decide the coordinates of these altered NACA0012 airfoils. Under specified plunging kinematics, it is observed that the increase of an airfoil thickness can reduce the leading edge vortex (LEV) in strength and delay the LEV shedding. The increase of the maximum thickness can enhance the time-averaged thrust coefficient and the propulsive efficiency without lift reduction. As the maximum thickness location moves towards the leading edge, the airfoil obtains a larger time-averaged thrust coefficient and a higher propulsive efficiency without changing the lift coefficient.
机译：为了研究翼型厚度对拍击性能的影响，模拟了从NACA0002翼型到NACA0020翼型的单翼系列的非稳态流场，该运动以纯直插运动进行了模拟，并使用纯直插运动模拟了一系列改变后的NACA0012翼型。计算流体动力学技术。使用“类函数/形状函数变换”参数方法来确定这些更改后的NACA0012机翼的坐标。在规定的下降运动学条件下，可以观察到机翼厚度的增加可以降低前缘涡流（LEV）的强度并延迟LEV脱落。最大厚度的增加可以在不减小升力的情况下提高时均推力系数和推进效率。随着最大厚度位置移向前缘，机翼在不改变升力系数的情况下获得了更大的时均推力系数和更高的推进效率。

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  • 来源
    《Mathematical Problems in Engineering》 |2010年第3期|p.569-587|共19页
  • 作者

    Liangyu Zhao; Shuxing Yang;

  • 作者单位

    School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, China;

    School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, China;

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  • 正文语种 eng
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