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赖怡,汪志成,毛捷先. 基于模拟退火算法的垂直轴风机翼型优化设计[J]. 科学技术与工程, 2021, 21(8): 3118-3123.
LaiYi,WangZhicheng,MaoJiexian.Optimum design of vertical axis wind turbine airfoil based on simulated annealing algorithm[J].Science Technology and Engineering,2021,21(8):3118-3123.
基于模拟退火算法的垂直轴风机翼型优化设计
Optimum design of vertical axis wind turbine airfoil based on simulated annealing algorithm
投稿时间:2020-07-06  修订日期:2021-02-23
DOI:
中文关键词:  垂直轴风力机  ? 翼型优化  ? 模拟退火算法  ? CST翼型建模方法
英文关键词:vertical axis wind turbine  airfoil optimization  simulated annealing algorithm  cst airfoil modeling method
基金项目:国家自然科学基金项目(51567001);江西省科技厅科技计划项目(20181BBE58006)
        
作者单位
赖怡 东华理工大学机械与电子工程学院
汪志成 东华理工大学机械与电子工程学院
毛捷先 东华理工大学机械与电子工程学院
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中文摘要:
      为了实现智能优化垂直轴风机翼型的气动特性,提高垂直轴风机的功率系数,通过模拟退火算法作为寻优方法,用气动性能计算工具XFOIL与MATLAB程序下的失速修正模型相结合用来计算翼型优化前后的气动特性,通过CST翼型建模法构建控制翼型曲线的翼型数学模型,选取翼型的控制参数为设计变量,翼型最大相对厚度以及最大相对厚度所处位置为约束条件,以翼型的最大升阻比为目标函数,建立翼型智能优化算法,并完成了对NACA0018翼型的优化设计。结果表明,优化后翼型的气动性能得到提高;最大升力系数提高了2%,升阻比的峰值提高了5.22%,最大切向力系数提高了6.77%。可见优化后翼型的失速性能得到了有效改善。
英文摘要:
      In order to make the aerodynamic characteristics of vertical axis wind turbine""s airfoil intelligence and improve the power factor of the vertical axis wind turbine, Simulated annealing algorithm was used to the optimization method, the aerodynamic performance calculation tool XFOIL is combined with the stall correction model under the MATLAB program to calculate the aerodynamic characteristics before and after airfoil optimization. The airfoil mathematical model for controlling the airfoil curve is constructed by the CST airfoil modeling method. The control parameters of the airfoil are selected as design variables. The maximum relative thickness of the airfoil and the location of the maximum relative thickness are the constraints. The resistance ratio is the objective function, an airfoil intelligent optimization algorithm is established, and the optimization design of the NACA0018 airfoil is completed. The results show that the aerodynamic performance of the optimized airfoil is improved, the maximum lift coefficient is increased by 2%, the peak lift-to-drag ratio is increased by 5.22%, and the maximum tangential force coefficient is increased by 6.77%. It is concluded that the stall performance of the optimized airfoil has been effectively improved.
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