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首页> 外文期刊>Journal of the American Helicopter Society >A Numerical Analysis of the Dynamic Stall Mechanisms on a Helicopter Rotor from Light to Deep Stall
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A Numerical Analysis of the Dynamic Stall Mechanisms on a Helicopter Rotor from Light to Deep Stall

机译：从光到深摊位直升机转子上动态失速机制的数值分析

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摘要

A loose coupling methodology between computational fluid dynamics and Comprehensive Analysis codes (elsA/HOST) is used to simulate a helicopter rotor in dynamic stall condition. Three stalled forward flight conditions have been selected in the wind tunnel 7A rotor test data to investigate the evolution of the stall mechanisms from a light stall to a deep stall condition. A decrease in the RPM is used to increase the rotor load. The lower the RPM the more severe the stall is. A double stall is observed in the lowest RPM case. The simulations are in satisfactory agreement with the experiment and are used to identify the mechanisms leading to the different stall events, notably the blade-vortex interaction. Rotormaps of the flow-separation regions are computed from numerical results, and similar regions of separated flow are observed in all the cases. These flow-separations originate from different aeroelastic mechanisms depending on their position on the rotor disk. As the rotor thrust coefficient is increased, some of these flow separations grow and lead to stall events.
机译：计算流体动力学和综合分析代码（ELSA /主机）之间的松散耦合方法用于模拟动态失速条件的直升机转子。在风洞7A转子测试数据中选择了三个停滞的前向飞行条件，以研究从轻型摊位到深度失速条件的失速机构的演变。 RPM的减少用于增加转子载荷。转速越低，档位越严重。在最低的RPM案例中观察到双重档位。模拟与实验令人满意的协议，用于识别导致不同失速事件的机制，特别是刀片 - 涡旋相互作用。从数值结果计算流动分离区域的ROSINAP，并且在所有情况下观察到类似的分离流区域。这些流动分离源自不同的空气弹性机构，这取决于它们在转子盘上的位置。随着转子推力系数的增加，这些流动分离中的一些生长并导致失速事件。

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