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首页> 外文期刊>Energy Conversion & Management >How to extract the angle attack on airfoils in cycloidal motion from a flow field solved with computational fluid dynamics? Development and verification of a robust computational procedure
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How to extract the angle attack on airfoils in cycloidal motion from a flow field solved with computational fluid dynamics? Development and verification of a robust computational procedure

机译：如何从计算流体动力学解决的流场中提取对翼型的角度攻击翼型中的翼型中的翼型攻击？强大的计算过程的开发和验证

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摘要

One of the key problems faced by researchers dealing with Computational Fluid Dynamics simulations and rotating machines is represented by how to extract the angle attack from a numerically computed flow field. If this issue has been addressed successfully for some applications, in case of airfoils moving in cycloidal motion (i.e. having a rotational motion within a rectilinear flow field, like in Darrieus Vertical-Axis Wind Turbines) some proposals do exist, but always affected by some arbitrary choices on the velocity probing that are not supported by a proper verification. The aim of the present study is to try finding a robust computational procedure tailored for the scope. To this end, three different post-processing methods - detailed in the study - were considered and applied to the flow fields of 2-blade H-Darrieus rotor, coming from a high-fidelity unsteady model based on Computational Fluid Dynamics; the resulting blade angle of attack trends over one rotor revolution were then combined with available blade forces data to assess the corresponding lift and drag coefficients. In order to assess the actual accuracy of these approaches for a stable tip-speed ratio, the post-processed force coefficients were compared to the ones computed via a numerical pitching airfoil model, which received the sampled angle of attack trends as input; eventually, the pitched lift and drag values have been used to reconstruct the blade forces over one rotor revolution and compare them with the ones coming from full turbine simulations. Results show large scattering of obtained data, remarking the importance of the proper selection of the angle of attack sampling strategy for the analysis of turbine performance. Overall, the "LineAverage" approach, i.e. the use of multiple sampling points around the airfoil for velocity probing, has proved to be the most accurate method.
机译：研究人员面临的关键问题之一，处理计算流体动力学模拟和旋转机器由如何从数值计算的流场中提取角度攻击来表示。如果已经成功地解决了某些应用程序的问题，则在翼型中移动的翼型（即在直线流场内具有旋转运动，如Darrieus垂直轴风力涡轮机），存在一些建议，但总是受到一些影响关于适当验证不支持的速度探测的任意选择。本研究的目的是尝试寻找针对范围量身定制的强大的计算过程。为此，三种不同的后处理方法 - 在研究中详述 - 被考虑并应用于基于计算流体动力学的高保真非稳定模型的2刀片H-Darrius转子的流场;然后将所得到的攻击趋势在一个转子旋转上方的攻击趋势与可用刀片强制数据组合以评估相应的提升和拖动系数。为了评估这些方法的实际精度，用于稳定的尖端速度比，将后处理的力系数与通过数值俯仰翼型模型计算的那些进行比较，该模型接收到输入的采样的攻击趋势角度;最终，倾斜升力和拖动值已经用于重建在一个转子旋转上方的刀片力，并将它们与来自完全涡轮机模拟的转子进行比较。 Results show large scattering of obtained data, remarking the importance of the proper selection of the angle of attack sampling strategy for the analysis of turbine performance.总的来说，“Lineforage”方法，即翼型围绕翼型的多个采样点进行速度探测，已被证明是最准确的方法。

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