风力机翼型动态失速数值模拟

INVESTIGATION OF DYNAMIC STALL OF WIND TURBINE AIRFOIL

在低雷诺数下,对NACA0012翼型和风力机专用翼型S809的动态失速进行数值模拟。研究不同网格密度、湍流模型对俯仰振荡翼型数值模拟的影响,并与实验结果进行对比验证。数值模拟得出的气动力迟滞曲线与实验结果变化趋势符合较好,表明了数值方法的有效性。采用此方法研究了北航自主开发的风力机专用翼型的动态失速特性。通过分析表明该翼型在动态失速过程中升力系数下降平缓,俯仰力矩振荡变化不显著,适合应用于兆瓦级大型风力机叶片。

Dynamic stall of NACA0012 airfoil and $809 airfoil at low Reynolds number were numerically investiga- ted. The effect ofdifferent grids and different turbulence models on numerical predictions of the lift, drag and pitch- ing moment coefficients was studied. The results accord with the experimental data prefreably and confirms that nu- merical simulation method is effective. The same method was applied to dynamic stall of BH-W airfoil developed by Beihang University. It is found that the lift coefficient decrease steadily and the pitching moment coefficients do not change significantly in the process of dynamic stall. The BH-W airfoil can be applied to blades of large-scale wind turbine.