选取NACA0012翼型为研究对象,对覆冰后翼型的三维流动特性和空气动力学特性进行研究。通过直流式风洞设备进行模型实验,明确不同来流速度下覆冰翼型的升阻力变化情况。通过STAR-CCM+软件对不同覆冰状态下的风力机叶片进行气动性能研究,分析覆冰对翼型表面压力系数、气动性能参数的影响。研究结果表明,明冰对叶片气动性能影响最为显著。以来流速度10 m/s分析,附着明冰时,翼型的升力系数降低34.9%,阻力系数增加97.2%;附着混合冰时,翼型的升力系数降低33.6%,阻力系数增加22.7%;附着霜冰时,翼型的升力系数降低24.1%,阻力系数增加27.2%。
Abstract
The NACA0012 airfoil was selected as the subject of study to investigate the three-dimensional flow characteristics and aerodynamic properties of iced airfoils. Model experiments were conducted using a direct-current wind tunnel to elucidate the changes in lift and drag forces of the iced airfoil under different incoming flow velocities. Aerodynamic performance studies on wind turbine blades under various icing conditions were carried out using the STAR-CCM+ software, analyzing the impact of icing on the surface pressure coefficients and aerodynamic performance parameters of the airfoil. The research findings indicated that the presence of clear ice had the most significant impact on the aerodynamic performance of the blades. At an incoming flow velocity of 10 m/s, the lift coefficient of the airfoil decreased by 34.9% and the drag coefficient increased by 97.2% with clear ice attachment; with mixed ice, the lift coefficient decreased by 33.6% and the drag coefficient increased by 22.7%; and with rime ice, the lift coefficient decreased by 24.1% and the drag coefficient increased by 27.2%.
关键词
风力机翼型 /
风洞实验 /
风电叶片 /
结冰数值计算 /
空气动力性能
Key words
wind turbines airfoil /
wind tunnel experiment /
wind turbine blades /
icing numerical calculation /
aerodynamics performance
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基金
国家自然科学基金（52071055）; 工信部高技术船舶科研项目（CBG2N21-2-2）
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