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The Application of Combined Momentum – Blade Element Theory for Aerodynamics Analysis Helicopter Rotor Blade in the Forward Flightud

机译：动量-叶片单元理论在飞行动力学分析中的应用直升机旋翼在前向飞行中的应用

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摘要

Present work introduced the aerodynamics analysis of rotor blade helicopter in forward flight. The analysis used a combination between a Momentum Theory and The Blade Element Theory. Here the inflow ratio was assumed a uniform over the disk plane and it was predicted by using the momentum Theory. As the inflow ratio is available, then by using the Blade element theory, the aerodynamics loading along the blade span of the rotor are computed, which finally the thrust coefficient CT can be obtained. For a given a rotor blade configuration and flight condition, the Thrust coefficient CT is unknown, while the momentum theory required this value to be known in predicting the inflow ratio. As result an iteration process is required in implementing those two combined approaches. For the assessment purposes, four test cases had been studied. The difference between one case to other case had been selected in term: 1) twist distribution, 2) the presence of coning angle and 3) the required aerodynamics characteristics. The result showed that the combination of Momentum Theory and The blade element theory could provide a fast solution in predicting the aerodynamics performance of rotor blade helicopter. However a comparison result with the experiment result was required in order to asses the degree of accuracy of this approach. This was suggested as future work.ud
机译：当前的工作介绍了旋翼直升机在前向飞行中的空气动力学分析。该分析结合了动量理论和叶片元素理论。在此，假设流入比率在整个磁盘平面上是均匀的，并且可以使用动量理论进行预测。在获得流入比的情况下，然后使用叶片单元理论，计算沿转子叶片跨度的空气动力学载荷，最终可以得出推力​​系数CT。对于给定的转子叶片配置和飞行条件，推力系数CT未知，而动量理论要求在预测流入比时需要知道该值。结果，在实现这两种组合方法时需要迭代过程。为了评估目的，研究了四个测试用例。一种情况与另一种情况之间的差异是根据以下条件选择的：1）扭曲分布，2）锥角的存在和3）所需的空气动力学特性。结果表明，动量理论和叶片元理论的结合可以为预测旋翼直升机的空气动力性能提供快速的解决方案。但是，需要与实验结果进行比较，以评估这种方法的准确性。建议将此作为将来的工作。 ud

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