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Design methodology using characteristic parameters control for low Reynolds number airfoils

机译：使用特征参数控制的低雷诺数机翼设计方法

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In the past century, low Reynolds number airfoil design for both military and civil applications has continued to capture the interest of practitioners of applied aerodynamics. A new design methodology for airfoils has been developed, which controls the airfoil profile through 8 parameters. The airfoil aerodynamic characteristics were predicted through the XFOIL code, to optimize airfoil under mode-FRONTIER environment. The reliability verification result predicted that the XFOIL code can be used to determine the airfoil performance in the linear segment of the lift coefficient curve. Application of this methodology was demonstrated through two cases. For Case-I, airfoils design were based on E387 airfoil profile and synthetic aerodynamic performance at different angles of attack for Re = 2.0 x 10(5) were considered. While for Case-II, designed airfoils were based on PSU 94-097 airfoil with synthetic aerodynamic performance at different angles of attack for Re = 4.0 x 10(5). Results of both cases showed enhanced aerodynamic properties for the designed airfoils. (C) 2019 Elsevier Masson SAS. All rights reserved.
机译：在过去的一个世纪中，用于军事和民用领域的低雷诺数翼型设计一直吸引着应用空气动力学从业者的兴趣。已经开发出一种新的机翼设计方法，该方法通过8个参数来控制机翼轮廓。通过XFOIL代码对机翼的空气动力特性进行了预测，以在模式前沿环境下优化机翼。可靠性验证结果表明，XFOIL代码可用于确定升力系数曲线线性段中的翼型性能。通过两个案例证明了该方法的应用。对于情况一，机翼设计基于E387机翼外形，并考虑了在Re = 2.0 x 10（5）的不同迎角下的合成空气动力性能。对于Case II，设计的机翼基于PSU 94-097机翼，在Re = 4.0 x 10（5）的不同迎角下具有合成空气动力学性能。两种情况的结果均表明设计翼型的空气动力学特性得到了增强。 （C）2019 Elsevier Masson SAS。版权所有。

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