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首页> 外文期刊>International journal of numerical methods for heat & fluid flow >Morphing airfoils analysis using dynamic meshing
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Morphing airfoils analysis using dynamic meshing

机译：使用动态网格化变形翼型分析

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Purpose - The purpose of this paper is to use dynamic meshing to perform CFD analyses of a NACA 0012 airfoil fitted with a morphing trailing edge (TE) flap when it undergoes static and time-dependent morphing. The steady CFD predictions of the original and morphing airfoils are validated against published data. The study also investigates an airfoil with a hinged TE flap for aerodynamic performance comparison. The study further extends to an unsteady CFD analysis of a dynamically morphing TE flap for proof-of-concept and also to realise its potential for future applications. Design/methodology/approach - An existing parametrization method was modified and implemented in a user-defined function (UDF) to perform dynamic meshing which is essential for morphing airfoil unsteady simulations. The results from the deformed mesh were verified to ensure the validity of the adopted mesh deformation method. ANSYS Fluent software was used to perform steady and unsteady analysis and the results were compared with computational predictions. Findings - Steady computational results are in good agreement with those from OpenFOAM for a non-morphing airfoil and for a morphed airfoil with a maximum TE deflection equal to 5 per cent of the chord. The results obtained by ANSYS Fluent show that an average of 6.5 per cent increase in lift-to-drag ratio is achieved, compared with a hinged flap airfoil with the same TE deflection. By using dynamic meshing, unsteady transient simulations reveal that the local flow field is influenced by the morphing motion. Originality/value - An airfoil parametrisation method was modified to introduce time-dependent morphing and used to drive dynamic meshing through an in-house-developed UDF. The morphed airfoil's superior aerodynamic performance was demonstrated in comparison with traditional hinged TE flap. A methodology was developed to perform unsteady transient analysis of a morphing airfoil at high angles of attack beyond stall and to compare with published data. Unsteady predictions have shown signs of rich flow features, paving the way for further research into the effects of a dynamic flap on the flow physics.
机译：目的-本文的目的是使用动态网格划分对装有变形后缘（TE）襟翼的NACA 0012机翼进行静态和随时间变化的变形进行CFD分析。原始机翼和变形机翼的稳定CFD预测已针对发布的数据进行了验证。该研究还研究了带有铰链TE襟翼的机翼，以比较空气动力性能。这项研究进一步扩展到动态变形TE襟翼的非稳态CFD分析，以进行概念验证，并实现其在未来应用中的潜力。设计/方法/方法-对现有的参数化方法进行了修改，并在用户定义的函数（UDF）中实施，以执行动态网格划分，这对于使机翼非稳态模拟变形至关重要。验证了变形网格的结果，以确保所采用的网格变形方法的有效性。 ANSYS Fluent软件用于执行稳态和非稳态分析，并将结果与​​计算预测进行比较。发现-对于非变形翼型和最大TE挠度等于弦的5％的变形翼型，稳定的计算结果与OpenFOAM的计算结果非常吻合。 ANSYS Fluent获得的结果表明，与具有相同TE挠度的铰接式襟翼翼型相比，升阻比平均提高了6.5％。通过使用动态网格划分，非稳态瞬态仿真表明，局部流场受变形运动的影响。原创性/价值-修改了机翼参数化方法，以引入随时间变化的变形，并通过内部开发的UDF驱动动态网格划分。与传统的铰链TE襟翼相比，该变形机翼具有出色的空气动力学性能。开发了一种方法，可以在失速以外的高攻角下对变形翼型进行非稳态瞬态分析，并与已发布的数据进行比较。不稳定的预测已经显示出丰富的流动特征的迹象，为进一步研究动态襟翼对流动物理的影响铺平了道路。

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