Gurney襟翼对风力机叶片翼型气动特性影响的数值模拟Numerical Simulation for the Influence of Gurney Flap on Aerodynamic Characteristic of Blade Aerofoil of Wind Turbine
王茜,皇甫凯林,徐璋,钟英杰
WANG Qian,HUANGFU Kai-lin,XU Zhang,ZHONG Ying-jie(Zhejiang University of Technology
摘要(Abstract)：
首先基于湍流模型对数值计算结果的影响,分别采用Spalart-Allmaras(S-A)和SST k-ω两种湍流模型对NA-CA0015翼型原型进行数值模拟,对比后选用了更为合适本算例的S-A湍流模型。然后对添加不同高度Gurney襟翼的NACA0015翼型改型进行数值模拟,高度分别为1%c、2%c和4%c(c为翼型弦长),厚度为2mm。结果表明,带有Gur-ney襟翼的翼型升力系数及升阻比均比原型有显著增加,并且明显改善了压力面和吸力面压力分布,在襟翼高度为2%翼型弦长时,可达到稳态下最佳升阻比的输出效果。
First of all,since the turbulence model affects numerical results,the NACA0015 airfoil is simulated by using Spalart-Allmaras and SST k-ω models separately.The differences between the two turbulence models are compared,and come to a more accurate S-A turbulence model to this airfoil.And then numerical simulations are carried out for NACA0015 aerofoil modification with different height of Gurney flap,the height of the flap is respectively 1%c、2%c and 4%c(chord length of blade),and thickness of 2mm.The result shows that the aerofoil with Gurney flap has significantly increased lift coefficient and lift-drag ratio compared with aerofoil prototype,and the pressure distributions of pressure surface and suction surface are notably improved.With height of the flap of 2% chord length,it can achieve the output in the best lift-drag ratio under steady state.
关键词(KeyWords)：
NACA0015翼型;Gurney襟翼;升阻比;升力系数
NACA0015 aerofoil;Gurney flap;lift-drag ratio;lift coefficient
基金项目(Foundation):
作者(Author):
王茜,皇甫凯林,徐璋,钟英杰
WANG Qian,HUANGFU Kai-lin,XU Zhang,ZHONG Ying-jie(Zhejiang University of Technology
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