摘要
为提高水平轴风力机的风能利用率,以NREL S809为原始翼型研究了分裂翼型缝道相对位置和缝道相对宽度对翼型流场结构、翼型气动性能、升力和阻力特性的影响。结果表明:分裂翼型缝道会对翼型周围涡的发展与变化产生影响,不仅能明显改善翼型的失速特性,还提高了翼型的气动性能;缝道相对位置为40/90、缝道相对宽度为1.0%时分裂翼型的升力系数达到最大,与原始翼型相比,其升力系数提高约10.797%,分裂作用对于提高翼型气动性能的效果较佳。
To improve the wind energy utilization of a horizontal axis wind turbine,taking the NREL S809 airfoil as a reference,the effects of relative position and relative width of split airfoil slot on following characteristics of the airfoil were studied,such as the flow field structure,aerodynamic performance,and lift and drag characteristics,etc.Results show that the split airfoil slot would affect the development and variation of vortices around the airfoil,which can not only improve the stall characteristics of the airfoil,but also enhance its aerodynamic performance.When the relative position and relative width of slot are relatively 40/90 and 1.0%,the lift coefficient of split airfoil would reach the maximum,which would be increased by 10.797%,compared with the original airfoil,with better splitting effect obtained in improving the aerodynamic performance of the airfoil.
作者
周伟
叶舟
王治红
李春
ZHOU Wei;YE Zhou;WANG Zhihong;LI Chun(School of Energy and Power Engineering,University of Shanghai for Science and Technology,Shanghai 200093,China;Shanghai Key Laboratory of Multiphase Flow and Heat Transfer in Power Engineering,Shanghai 200093,China;No.703 Research Institute of CSIC,Harbin 150078,China)
出处
《动力工程学报》
CAS
CSCD
北大核心
2019年第6期478-485,共8页
Journal of Chinese Society of Power Engineering
基金
国家自然科学基金资助项目(51676131,51176129)
上海市科委资助项目(13DZ2260900)
关键词
分裂翼型
缝道
相对位置
宽度
气动性能
split airfoil
slot
relative position
width
aerodynamic performance
