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首页> 外文期刊>Proceedings of the Institution of Mechanical Engineers >Numerical investigation of Gurney flap influences on aerodynamic performance of a pitching airfoil in low Reynolds number flow
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Numerical investigation of Gurney flap influences on aerodynamic performance of a pitching airfoil in low Reynolds number flow

机译：葛谷襟翼对低雷诺数流动盆翼翼型空气动力学性能的数值研究

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摘要

The main purpose of present work is to investigate the aerodynamic performance of a pitching NACA 0012 airfoil equipped with a Gurney flap in flow with low Reynolds number. The aerodynamic influences of flap location, mounting angle, and height are numerically studied. In this regard, a Lagrangian-Eulerian pressure-based numerical algorithm is developed on hybrid grids attached to a pitching solid boundary. A finite volume-based finite element method is used to discretize the governing equations. As reported in previously related studies, this unified algorithm could be used to solve the unsteady incompressible flow in domains with moving mesh and/or moving boundary with sufficient robustness and accuracy. The other advantage of this algorithm is that it does not need any type of dissipation term and/or damping function. Using this unified algorithm, the numerical experiments indicate that the Gurney flap increases the lift and drag coefficients and enhances the aerodynamic efficiency. The best aerodynamic performance is predicted for the case in which the flap is located at trailing edge with the mounting angle of 90 degrees. The flap height is predicted to have different and most impacts on aerodynamic efficiency during upstroke and downstroke. The numerical results show that the airfoils equipped by flaps with height between 6% and 12% of the airfoil chord are the most aerodynamically efficient airfoils. Changing of lift and drag coefficients are due to increase of effective camber and thickness in all cases.
机译：目前工作的主要目的是研究俯仰Naca 0012翼型的空气动力学性能，配备有低雷诺数的盖齿瓣。在数值研究了翼片位置，安装角度和高度的空气动力学影响。在这方面，在连接到俯仰固网上的混合网格上开发了一种基于拉格朗日 - 欧拉压力的数值算法。基于有限的体积的有限元方法用于离散化程方程。如先前相关的研究报告，该统一算法可用于解决具有移动网格和/或移动边界的域中的不稳定不可压缩流量，具有足够的鲁棒性和准确性。该算法的另一个优点是它不需要任何类型的耗散术语和/或阻尼功能。使用该统一算法，数值实验表明，盖尼挡板增加了提升和拖曳系数并提高了空气动力学效率。对于翼片位于后缘的情况下，预测最佳空气动力学性能，其安装角度为90度。预测翼片高度对上行程和下行程期间对空气动力学效率的不同和影响。数值结果表明，由翼片配备的翼型，高度为6％和12％的翼型弦是最空气动力学有效的翼型。电梯和拖动系数的变化是由于所有情况下有效的弯曲和厚度的增加。

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