Flatback airfoil wind tunnel experiment.
Flatback airfoil wind tunnel experiment.
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DOI：
10.2172/933221
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发表时间：
2008-04
期刊：
影响因子：
--
通讯作者：
E. Mayda;C. V. Dam;D. Chao;D. Berg
中科院分区：
文献类型：
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作者：
E. Mayda;C. V. Dam;D. Chao;D. Berg
本文介绍了在加州大学戴维斯分校风洞试验段中对弦雷诺数为一百万的厚风力涡轮机截面形状进行的计算流体动力学研究。本研究的目的是验证高固体堵塞条件下的标准风洞壁修正，并在建立风洞模型和进行实验之前，重申钝后缘或平背对典型厚翼型性能特性的有利影响。数值模拟证明了标准风洞修正对于在10%固体阻塞比下40%最大厚度弦比翼型的拟议试验是有效的。对尖后缘基线翼型和推导出的平背翼型的计算升力特性的比较，再次证实了早先观察到的随后缘厚度增加对表面污染敏感性降低的趋势。
A computational fluid dynamics study of thick wind turbine section shapes in the test section of the UC Davis wind tunnel at a chord Reynolds number of one million is presented. The goals of this study are to validate standard wind tunnel wall corrections for high solid blockage conditions and to reaffirm the favorable effect of a blunt trailing edge or flatback on the performance characteristics of a representative thick airfoil shape prior to building the wind tunnel models and conducting the experiment. The numerical simulations prove the standard wind tunnel corrections to be largely valid for the proposed test of 40% maximum thickness to chord ratio airfoils at a solid blockage ratio of 10%. Comparison of the computed lift characteristics of a sharp trailing edge baseline airfoil and derived flatback airfoils reaffirms the earlier observed trend of reduced sensitivity to surface contamination with increasing trailing edge thickness.