垂直轴风力机翼型气动优化设计  

Optimization Design on Airfoil of Vertical Axis Wind Turbine

作　　者：梁昌平[1] 席德科[1] 张森[1] 陈宝峰 王向前 郭青陇 

机构地区：[1]西北工业大学航空学院,陕西西安710072 [2]山西焦煤安瑞电气风机有限公司,山西运城044402

出　　处：《航空计算技术》2016年第5期17-20,共4页Aeronautical Computing Technique

摘　　要：对小型垂直轴风力机常用的NACA0015翼型进行优化设计,使其具有更优的气动性能。在优化过程中,利用CST参数化方法对翼型的几何外形进行扰动,选取翼型的厚度及弯度作为约束,翼型切向力系数作为目标函数,以基于非支配排序的遗传算法(NSGA-II)作为优化方法,最后建立优化流程,优化过程中利用XFOIL程序结合Viterna-Corrigan失速后模型计算优化前后翼型的气动性能。结果表明,与NACA0015翼型相比,优化后的翼型气动性能有了较大提升,最大升力系数提高了6.63%,最大升阻比提高了27.5%,最大切向力系数提高了22.7%。Optimizing the NACA0015 airfoil which is widely applied in small-scale vertical axis wind turbine to make it have a better aerodynamic performance. In the optimization process, using CST parameterization to perturb the airfoil geometry, the thickness and camber of the airfoil are selected as the constraint, and the value of the tangential force coefficient is chosen as the objective function ,the genetic algorithm based on non-dominated sorting （NSGA -II）is selected as an optimization method, and the optimizing process is established lastly, calculates the aerodynamic performance of the airfoil by applying the approach of combining XFOIL program and Viterna- Corrigan post- stall mode. The result illustrates that, compared with the NACA0015 airfoil, the aerodynamic performance of the optimized airfoil has been greatly improved, the maximum lift coefficient, the maximum lift- drag ratio and the maximum tangential force coefficient are increased by 6.63% ,27.5% and 22.7% ,respectively.

关 键 词：垂直轴风力机 CST参数化方法 NSGA-II算法 翼型 优化 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]