In this study, the aerodynamic performance of bionic airfoil was numerically studied by CFD method. The bionic airfoil was represented by the combination of airfoil and a small trailing edge flap. A variety of configurations were calculated to study the effect of flap parameters, such as the flap angle, position, and shape, on the bionic airfoil aerodynamic characteristics based on two layouts which were that (1) there was a tiny gap between the airfoil and the flap and (2) there was no gap between the two. The results showed that the flap angle and position had significant effects on the aerodynamic performance of the airfoil with the two layouts. Compared with the clean airfoil, the maximum lift coefficients of the first layout and the second layout could be increased by 10.9% and 7.9%, respectively. And the effective angle of attack (AoA) range for improving the lift-to-drag ratio could reach 7°. The flap shape also affected the airfoil aerodynamic characteristics, and the flap with the sinusoid curve shape showed ideal performance.

中文翻译：

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仿生翼型上流动的数值模拟

本研究采用CFD方法对仿生翼型的气动性能进行了数值研究。仿生翼型由翼型和小后缘襟翼的组合代表。计算了多种配置以研究襟翼角度、位置和形状等襟翼参数对仿生翼型气动特性的影响，基于两种布局：（1）翼型和翼型之间存在微小间隙。皮瓣和 (2) 两者之间没有间隙。结果表明，襟翼角度和位置对两种布局的翼型气动性能有显着影响。与清洁翼型相比，第一种布局和第二种布局的最大升力系数分别提高了10.9%和7.9%。并且提高升阻比的有效攻角（AoA）范围可以达到7°。襟翼形状也影响翼型气动特性，正弦曲线形状的襟翼表现出理想的性能。