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Effect of winglets induced tip vortex structure on the performance of subsonic wings

机译：小翼诱导的尖端涡结构对亚音速机翼性能的影响

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This paper presents the comparative study of the effectiveness of three different winglet designs in reducing lift induced drag by changing the number of vortices and vortex distribution at the wingtip and correlating it to the aerodynamic characteristics of the baseline wing. The best three winglet geometries are appended to wings of different aspect ratio to further study their effectiveness in reducing drag and augmenting the lift coefficient. Computational simulations were performed on Ansys Fluent V15 using the Reynolds Averaged Navier-Stokes equations coupled with the k-omega SST turbulence model to study the three dimensional flow and vortex structure about the half wing. The simulation shows that there is a strong relationship between the size of the tip vortex and the aerodynamic parameters such as lift, drag and pitching moment of the wing. The multi-tipped wing is the most effective at dispersing the vortice energy and reducing the induced drag. Optimization of the number of tips was found to be crucial to increase the lift coefficient while reducing the contributions of frictional and vortex drag. Although the lift was found to be increasing with the number of tips, the rise in frictional drag due to wetted surface area is a limiting factor towards aerodynamic efficiency. The results show that the multi tip-4 is most capable at increasing the lift coefficient, but is surpassed by multi-tip-3 in lift to drag ratio. As aerodynamic efficiency is key for improving flight range and duration, it is concluded that multi-tip-3 is the optimum winglet for the given design conditions. The baseline wings show maximum performance at higher aspect ratios. Overall, winglets are found to be more effective at lower aspect ratio and provide highest improvement in aerodynamic efficiency at a moderate aspect ratio of 10. (C) 2016 Elsevier Masson SAS. All rights reserved.
机译：本文通过改变翼尖的涡流数量和涡流分布并将其与基线机翼的空气动力学特性相关联，对三种不同的小翼设计在降低升力引起的阻力方面的有效性进行了比较研究。最好的三个小翼几何形状附加到不同长宽比的机翼上，以进一步研究它们在减少阻力和增加升力系数方面的有效性。使用Reynolds平均Navier-Stokes方程和k-omega SST湍流模型在Ansys Fluent V15上进行了计算仿真，以研究半机翼的三维流动和涡流结构。仿真表明，尖端涡旋的大小与空气动力学参数（如机翼的升力，阻力和俯仰力矩）之间存在很强的关系。多翼机翼在散布调味酱能量和减少诱导阻力方面最有效。发现叶尖数量的优化对于增加升力系数同时减少摩擦阻力和涡流阻力至关重要。尽管发现升程随着叶尖数量的增加而增加，但是由于湿润的表面积导致的摩擦阻力的增加是空气动力学效率的限制因素。结果表明，多尖端4在提升升力系数方面最有能力，但在升阻比方面却被多尖端3所超越。由于空气动力学效率是改善飞行距离和持续时间的关键，因此得出结论，在给定的设计条件下，multi-tip-3是最佳的小翼。基线机翼在较高的宽高比下显示出最佳性能。总体而言，发现小翼在较低的长宽比下更有效，并且在中等长宽比为10时可最大程度地提高空气动力学效率。（C）2016 Elsevier Masson SAS。版权所有。

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