Wind Tunnel Testing of Airfoils for Wind Turbine Applications
Wind Tunnel Testing of Airfoils for Wind Turbine Applications
复制标题
风力涡轮机应用翼型件的风洞测试
DOI：
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发表时间：
2015
期刊：
影响因子：
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通讯作者：
W. Devenport
中科院分区：
文献类型：
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作者：
M. Kuester;K. Brown;T. Meyers;N. Intaratep;Aurélien Borgoltz;W. Devenport
翼型截面升力和阻力的准确风洞测量对于风力涡轮机叶片的设计和性能评估至关重要。随着叶片尺寸的不断增大，对雷诺数逐渐增大时的高精度风洞试验结果的需求也在增加。进行这些风洞测量需要精确的实验控制，这些测量的三个挑战是模型表面质量，测压孔效应和模型在气动载荷下的偏转。在弗吉尼亚理工大学的稳定性风洞中，采用弦雷诺数（Rec）为3.0 × 106的DU 96-W-180翼型几何形状，对这些挑战进行了系统的研究。萘升华表现出由表面缺陷引起的湍流楔;去除这些缺陷使升力曲线斜率增加3%。通过将不同尺寸的测压孔放置在翼型上相同的弦位置，研究了测压孔直径的影响。这些测量结果表明，当在湍流边界层中进行测量时，与抽头直径相关的稳定压力偏差，并且萘可视化显示了由前缘处的压力抽头产生的湍流楔。最后，激光距离传感器用于测量模型在气动载荷下的偏转/旋转，改进了传统的攻角测量。解决这些挑战提高了稳定性风洞中升力测量的准确性，并强调了在进行这些类型的风洞测量时需要精确的实验控制。
Accurate wind tunnel measurements of the lift and drag of airfoil sections are critical for the design and performance evaluation of wind turbine blades. As blades continue to increase in size, the demand for highly accurate wind tunnel results at progressively larger Reynolds numbers has also increased. Performing these wind tunnel measurements requires precise experimental control, and three challenges for these measurements are model surface quality, pressure tap effects, and model deflections under aerodynamic loading. These challenges were systematically studied in the Virginia Tech Stability Wind Tunnel using a DU96-W-180 airfoil geometry at a chord Reynolds number (Rec) of 3.0 × 106. Naphthalene sublimation showed turbulent wedges caused by surface imperfections; removing these imperfections increased the lift curve slope by 3%. Pressure tap diameter effects were investigated by placing taps of varying size at the same chord location on the airfoil. These measurements showed a steady pressure bias correlated to tap diameter when making measurements in turbulent boundary layers, and naphthalene visualizations showed a turbulent wedge created by pressure taps at the leading edge. Finally, laser distance sensors were used to measure model deflections/rotations under aerodynamic loading, improving upon the traditional angle of attack measurement. Addressing these challenges has improved the accuracy of lift measurements in the Stability Wind Tunnel and emphasized the need for precise experimental controls when performing these types of wind tunnel measurements.