基于k-ω SST湍流模型,利用商业CFD工具ANSYS Fluent 16.0对DU35-17原始翼型、钝尾缘修型翼型及布置V型沟槽钝尾缘翼型进行数值模拟计算,对翼型改进前后的升阻力系数、流场分布和表面压力系数进行对比分析。结果表明,翼型在钝尾缘修型的同时布置V型沟槽,通过改变翼型尾缘处的压力分布和翼型表面的流动分布,对流动分离的抑制有积极影响;布置V型沟槽钝尾缘翼型能增大翼型上下翼面的压力系数差值,降低翼型边界层内因气体黏性所产生的流动减速现象,从而达到减阻增升的效果;布置V型沟槽可有效增大最大升力系数和失速攻角,减小前缘压力波动,提高翼型气动性能。
Abstract
Based on the k-ω SST turbulence model, use the commercial CFD tool ANSYS Fluent 16.0 to numerically simulate the DU35-17 original airfoil, blunt trailing edge modified airfoil, and V-groove blunt trailing edge airfoil. The lift-drag coefficient, flow field distribution and surface pressure coefficient before and after the airfoil modification are compared and analyzed. The results show that the airfoil is configured with V-grooves while blunt trailing edge modification is performed. By changing the pressure distribution at the airfoil trailing edge and the flow distribution on the airfoil surface, it has a positive effect on the suppression of flow separation. The blunt trailing edge airfoil with V-groove can increase the pressure coefficient difference between the upper and lower airfoil surfaces of the airfoil, and reduce the flow deceleration caused by the gas viscosity in the airfoil boundary layer, thereby achieving the effect of reducing drag and increasing rise. To arrange V-grooves can effectively improve the maximum lift coefficient and stall angle of attack, reduce the leading edge pressure fluctuations, and improve the aerodynamic performance of the airfoil.
关键词
风力机 /
翼型 /
减阻 /
数值模拟 /
V型沟槽 /
钝尾缘翼型 /
气动性能
Key words
wind turbines /
airfoil /
drag reduction /
numerical simulation /
V-groove /
blunt trailing edge airfoils /
aerodynamic performance
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基金
国家国际科技合作专项（2014DFR60990）; 国家自然科学基金（51565028）; 国家自然科学基金（51965034）; 甘肃省科技厅重大专项（17ZD2GA006）
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