前缘涡流发生器对S809翼型气动性能影响的研究

Investigation of the Impact of Leading Edge Vortex Generators on the Aerodynamic Performance of the S809 Airfoil

摘要: 本文采用DDES模型和STAR CCM+软件，对装配前缘涡流发生器的S809翼型在不同攻角下的气动性能进行了研究。结果表明，前缘涡流发生器能显著提升翼型在20˚攻角及以下的升力系数和降低阻力系数，特别是在20˚攻角下，升力系数提升了64.1%，阻力系数降低了50.5%。然而，随着攻角增加至24˚及以上，涡流发生器控制流动分离的效果逐渐减弱。该研究不仅验证了前缘涡流发生器在控制流动分离方面的有效性，也为风力机叶片的设计提供了重要的参考依据。未来研究将进一步探讨涡流发生器的尺寸、形状及布置方式对其性能的影响，及其在实际风力机叶片中的应用潜力。

Abstract: This paper utilizes the DDES model and STAR CCM+ software to study the aerodynamic performance of the S809 airfoil equipped with leading-edge vortex generators at various angles of attack. The results show that the leading-edge vortex generators significantly enhance the lift coefficient and reduce the drag coefficient at angles of attack of 20˚ and below, particularly at a 20˚ angle of attack where the lift coefficient increased by 64.1% and the drag coefficient decreased by 50.5%. However, as the angle of attack increases to 24˚ and above, the effectiveness of the vortex generators in controlling flow separation gradually diminishes. This study not only verifies the effectiveness of leading-edge vortex generators in controlling flow separation but also provides important reference data for the design of wind turbine blades. Future research will further explore the impact of the size, shape, and arrangement of vortex generators on their performance, as well as their potential application in actual wind turbine blades.