摘要
为满足风力机叶片性能、结构及工艺的需求,叶片后缘厚度要进行改型。本文采用Rfoil软件计算后缘改型前后的DU93-W-210翼型气动性能,研究分析了后缘改型从吸力面向压力面偏移以及改型位置从前缘向后缘偏移对翼型气动特性的影响。不同的后缘厚度改型方法对翼型气动性能的影响不同。研究结果表明,对于期望得到较好的升力系数的改型方法,以偏向压力面和改型位置靠近最大厚度为佳;而对于增强叶尖的工艺性且气动性能的改变尽量小的改型方法,则以对称增厚为宜;此外,后缘厚度改型后的升力系数和升力系数线性段斜率呈负相关关系。
Due to the requirements of performance, structure and technology, the thickness of the trailing edge of wind turbine blade airfoil should be modified. In this paper, the aerodynamic performance of the DU93-W-210 airfoil before and after the trailing edge modification was calculated using Rfoil software. The effects of the trailing edge modification shifting from suction to pressure surface and the modification position shifting from the leading edge to the trailing edge on the aerodynamic characteristics of the airfoil were studied and analyzed. Different trailing edge thickness modification methods have different effects on the aerodynamic performance of the airfoil. The results show that, for the modification method that expects to get a better lift coefficient, it is better to lean towards the pressure surface and near the maximum thickness;for the modification method that enhances the blade tip technology and the change of aerodynamic performance as little as possible, symmetrical thickening is appropriate. In addition, there is a negative correlation between the lift coefficient and the slope of the linear section of the lift coefficient curve after the trailing edge thickness modification.
出处
《国际航空航天科学》
2023年第4期111-116,共6页
Journal of Aerospace Science and Technology
