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首页> 外文期刊>Journal of the American Helicopter Society >Passive Flow Control of Dynamic Stall via Surface-Based Trapped Vortex Generators
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Passive Flow Control of Dynamic Stall via Surface-Based Trapped Vortex Generators

机译：通过基于面的陷阱涡发生器对动态失速的被动流量控制

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摘要

A novel passive flow control concept-based on the local modification of an airfoil's surface-is proposed and examined via computational fluid dynamics (CFD) for the mitigation of the negative effects of dynamic stall, i.e., for the reduction of peak negative pitching moment while not deteriorating significantly the original lift and drag characteristics. Two-dimensional CFD simulations of a NACA 0012 airfoil exposed to a freestream of Mach 0.3 and Re = 3.76 x 10(6) and undergoing a 15 degrees +10 degrees pitch oscillation with a reduced frequency of 0.101 were conducted. The baseline airfoil simulations were carefully verified and validated, showing excellent agreement with wind tunnel data. Twenty-six different local geometry modifications were proposed and examined, all functioning as a trapped-vortex generator. The surface modifications were examined on both the upper and lower surfaces. In the case of the upper surface modifications, the best geometries could reduce the peak negative pitching moment by as much as 37-63%, while sacrificing only 2-10% of peak lift and reducing drag by 14-38%. On the other hand, the lower surface modifications demonstrated the ability to increase lift by 4-16% with only minor penalty in pitching moment and drag.
机译：提出并提出了一种基于机翼表面局部修改的新型被动流量控制概念，并通过计算流体力学（CFD）对其进行了研究，以减轻动态失速的负面影响，即降低峰值负俯仰力矩的同时不会显着恶化原始的提升和阻力特性。进行了NACA 0012机翼的二维CFD模拟，该机翼暴露于0.3马赫数和Re = 3.76 x 10（6）的自由流中，并经历了15度+10度的俯仰振荡，频率降低了0.101。基准翼型模拟经过仔细验证和验证，显示出与风洞数据的极佳一致性。提出并检查了26种不同的局部几何形状修改，所有这些修改都起着陷阱涡发生器的作用。在上表面和下表面上都检查了表面改性。在上表面修改的情况下，最佳的几何形状可以将峰值负俯仰力矩减少多达37-63％，而仅牺牲峰值提升的2-10％并将阻力减少14-38％。另一方面，较低的表面改性表现出将升力提高4-16％的能力，而俯仰力矩和阻力只有很小的损失。

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