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Effect of Blade Number on Induced Power in Hover

机译：叶片数对悬停时感应功率的影响

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摘要

Hover performance is thought to be primarily affected by rotor solidity, and it has been suggested that the blade number does not have any effect on performance while comparing rotors with the same solidity. Vortex theory inherently includes the blade number effect but does not account for chord or solidity. For example, Goldstein's classical theory for lightly loaded propellers shows the effect of blade number (independent from blade chord or solidity) on optimum loading and induced power. Simpler analytical formulations, while less accurate, are more useful for understanding these effects. This paper employs combined blade element momentum theory augmented with a finite blade number or "tip loss" effect, using Prandtl's approximation to Goldstein's theory to study induced power in hover. An examination of induced flow effects resulting from finite blade number suggests, contrary to conventional wisdom, that blade number, and not just solidity, has a primary influence on the induced power in hover. Blade aspect ratio or mean nondimensional chord, the other constituent in solidity, appears to have a much smaller and secondary influence. This paper further addresses similarity considerations that can be applied to understand induced power trends.
机译：悬停性能被认为主要受转子坚固性的影响，并且已经提出，在比较具有相同坚固性的转子时，叶片数量对性能没有任何影响。涡旋理论固有地包括叶片数效应，但不考虑和弦或坚固性。例如，戈德斯坦（Goldstein）的轻载螺旋桨经典理论表明，叶片数量（独立于叶片弦或固体）对最佳载荷和感应功率的影响。较简单的分析公式虽然准确性较低，但对于理解这些效果更有用。本文采用结合有限元叶片数或“叶尖损失”效应的叶片要素动量理论，并利用Prandtl对Goldstein理论的近似来研究悬停时的感应功率。与常规观点相反，检查由有限叶片数引起的感应流动效应表明，叶片数而不是坚固性对悬停时的感应功率有主要影响。叶片的纵横比或平均无量纲，坚固性中的其他组成部分，似乎具有较小和次要的影响。本文进一步讨论了可用于理解感应功率趋势的相似性考虑因素。

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