Computational Investigation of Finite Width Microtabs for Aerodynamic Load Control
Computational Investigation of Finite Width Microtabs for Aerodynamic Load Control
复制标题
用于气动载荷控制的有限宽度微片的计算研究
DOI：
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发表时间：
2005
期刊：
影响因子：
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通讯作者：
D. Nakafuji
中科院分区：
文献类型：
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作者：
E. Mayda;C. V. Dam;D. Nakafuji
出于主动负载控制的目的，已经提出在风力涡轮机叶片上使用可展开的微型片。为了研究翼片对翼型截面气动性能特性的影响，已经进行了大量的二维风洞试验和CFD模拟。本文对现有研究进行了文献调查，这些研究着眼于在拉环上引入间隙和锯齿的影响。发现这样的处理允许调整拉片的升力增强特性。描述了应用于翼型的各种翼片间隙配置的三维雷诺平均纳维-斯托克斯计算，并给出了结果。发现翼片密实度比和升力增量之间的关系是高度线性的。这种关系对于未来 microtab 部署系统的开发可能具有重要意义。
The use of deployable microtabs on wind turbine blades has been proposed for the purpose of active load control. A great deal of two-dimensional wind tunnel testing and CFD simulation has already been conducted to study the effects of tabs on the aerodynamic performance characteristics of airfoil sections. This paper presents a literature survey of existing studies that have looked at the effects of introducing gaps and serrations to the tabs. Such treatments are found to allow modulation of the lift enhancing properties of the tab. Three-dimensional Reynolds-averaged Navier-Stokes calculations of various tabgap configurations applied to an airfoil are described, and results are presented. The relationship between tab solidity ratio and increments in lift is found to be highly linear. Such a relationship could be significant for the development of future microtab deployment systems.