Two-Dimensional Wind Tunnel and Computational Investigation of a Microtab Modified Airfoil
Two-Dimensional Wind Tunnel and Computational Investigation of a Microtab Modified Airfoil
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Microtab 改进翼型件的二维风洞和计算研究
DOI：
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发表时间：
2005
期刊：
影响因子：
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通讯作者：
C. V. Dam
中科院分区：
文献类型：
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作者：
B. Paul;K. Standish;C. V. Dam
*†本文介绍了一种基于微型翼片的气动载荷控制系统的有效性的计算和风洞研究。基于微型翼片的载荷控制概念包括一个小翼片，其展开高度约为翼弦的1%，在后缘附近近似垂直于升力面出现。通过在升力表面的上（吸力）表面上部署翼片来实现升力减轻。类似地，升力增强可以通过在升力表面的下（压力）表面上展开翼片来实现。采用雷诺平均纳维尔-斯托克斯方法进行了灵敏度分析，以确定S809基准翼型在100万弦雷诺数时主动载荷控制的调整片的最佳尺寸和位置。在S809翼型的风洞研究过程中，这些数值模拟提供了对控制这种有前途的载荷控制系统和导向翼片位置的流动现象的深入了解。数值和实验结果基本一致，并证明通过微凸片进行负载控制是可行的。未来的工作将包括研究翼片展开和收缩过程中发生的非定常载荷变化，以及涉及翼片展向位置和翼片间隙的三维问题。
*† ‡ A computational and wind tunnel investigation into the effectiveness of a microtab-based aerodynamic load control system is presented. The microtab-based load control concept consists of a small tab, with a deployment height on the order of 1% of chord, which emerges approximately perpendicular to a lifting surface in the vicinity of the trailing edge. Lift mitigation is achieved by deploying the tabs on the upper (suction) surface of a lifting surface. Similarly, lift enhancement can be attained by tab deployment on the lower (pressure) surface of a lifting surface. A sensitivity analysis using Reynolds-averaged NavierStokes methods was conducted to determine optimal sizing and positioning of the tabs for active load control at a chord Reynolds number of 1.0 million for the S809 baseline airfoil. These numerical simulations provide insight into the flow phenomena that govern this promising load control system and guided tab placement during the wind tunnel study of the S809 airfoil. The numerical and experimental results are largely in agreement and demonstrate that load control through microtabs is viable. Future efforts will include a study of the unsteady load variations that occur during tab deployment and retraction, and three-dimensional issues involving spanwise tab placement and tab gaps.