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A computational procedure to define the incidence angle on airfoils rotating around an axis orthogonal to flow direction

机译：确定绕垂直于流向的轴旋转的翼型的入射角的计算程序

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摘要

Numerical simulations provided in the last few years a significant contribution for a better understanding of many phenomena connected to the flow past rotating blades. In case of airfoils rotating around an axis orthogonal to flow direction, one of the most critical issues is represented by the definition of the incidence angle on the airfoil from the computed flow field. Incidence indeed changes continuously as a function of the azimuthal position of the blade and a distribution of peripheral speed is experienced along the airfoil's thickness due to radius variation. The possibility of reducing the flow to lumped parameters (relative speed modulus and direction), however, would be of capital relevance to transpose accurate CFD numerical results into effective inputs to low-order models that are often exploited for preliminary design analyses. If several techniques are available for this scope in the case of blades rotating around an axis parallel to flow direction (e.g., horizontal-axis wind turbines), the definition of a robust procedure in case the revolution axis is orthogonal to the flow is still missing.
机译：过去几年中提供的数值模拟为更好地理解与流过旋转叶片的流有关的许多现象做出了重大贡献。在翼型绕正交于流动方向的轴线旋转的情况下，最关键的问题之一是通过计算流场定义翼型的入射角。实际上，入射角是根据叶片的方位角位置连续变化的，并且由于半径的变化，沿机翼的厚度会经历圆周速度的分布。但是，将流量减少到集总参数（相对速度模量和方向）的可能性与将准确的CFD数值结果转换为低阶模型的有效输入（对于经常用于初步设计分析的有效输入）具有资本意义。如果在叶片绕平行于流向的轴旋转的情况下（例如水平轴风力涡轮机）有几种技术可用于此范围，则仍然缺少在旋转轴与流正交的情况下进行稳健过程的定义。

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