摘要
针对风力机叶片翼型S809以及95%弦长位置处加载小插片的翼型进行详细的数值模拟研究,选用合适的SST湍流模型,对加载小插片后的翼型在不同攻角下的流场进行了详细分析,总结小插片对翼型气动特性的影响,进而提出小插片影响翼型流动、提升翼型升力的机理。研究表明,带小插片翼型提升升力的机理在于,改变了翼型的库塔条件,使后驻点位置出现在微型小插片末端,有效地增加了气动曲面轮廓和环量。计算结果还表明小插片在翼型的正常工作范围才起作用。
This paper used numerical methods to investigate the flow field around wind turbine airfoil S809 and the airfoil with micro tab at 95% chord at the pressure side neat the trailing edge. The adaptive SST turbulence model was chosen to analyze the detailed flow field of the two airfoils under different angles of attack. The effect of the micro tab was brought out, and then the lift arising mechanism of the micro tab was presented. The results showed that the lift arising mechanism of the micro tab lied on the change of Kut- ta condition of the airfoil. The micro tab made the stagnation point move to the end of the micro tab, which made the aerodynamic profile and circulation increased. Meanwhile, the micro tab only availed at the normal working condition.
出处
《空气动力学学报》
EI
CSCD
北大核心
2012年第6期786-791,共6页
Acta Aerodynamica Sinica
基金
国家自然科学基金(51076101)
