基于CFD方法的低雷诺数下NACA4412翼型升、阻力系数图谱  

Map of lift and drag coefficient of NACA4412 airfoil at low reynolds number based on CFD

作　　者：陈哲 郭子伟[1,2,3] 何炎平[1,2,3] 孟龙 赵永生[1,2,3] 

机构地区：[1]上海交通大学海洋工程国家重点实验室,上海200240 [2]高新船舶与深海开发装备协同创新中心(船海协创中心),上海200240 [3]上海交通大学船舶海洋与建筑工程学院,上海200240

出　　处：《可再生能源》2018年第2期296-301,共6页Renewable Energy Resources

基　　金：国家重点基础研究发展计划资助项目(2014CB046200)

摘　　要：在浮式风力机模型试验中,采用重新设计模型叶片的方式满足模型尺寸下风力机空气动力性能相似。所选用翼型在低雷诺数条件下升、阻力系数的准确性是叶片优化设计过程中的关键。文章以NACA4412翼型为例,对比常用的翼型升、阻力系数计算方法,得出XFOIL软件计算快、准确度低,而基于Fluent的2D RANS方法准确度高、时间长的结论。考虑不同雷诺数、不同攻角下升、阻力系数计算工作量大,文章提出基于CFD方法的NACA4412翼型在低雷诺数下升、阻力系数图谱。利用图谱可以在短时间内得到准确度高的升、阻力系数,为基于NACA4412翼型的单翼型模型叶片优化设计提供技术资料。In the model tests of floating wind turbines,designing the aerodynamic contour of the model blade is used to satisfy the aerodynamic similitude. The accuracy of lift and drag coefficient is the key part of optimum design of blades.Comparing the common calculation method of lift and drag coefficient of NACA4412 airfoil,this paper gets that the method based on XFOIL can get the data quickly but in low accuracy and the method based on Fluentcan get more accurate results but in long time. Considering the amount of calculation of lift and drag coefficient at different Reynolds number and angle of attack,this paper puts forward a map of lift and drag coefficient of NACA4412 airfoil at low Reynolds number based on CFD. It can get more accurate results in a relatively short time. It provides technical information for the optimum design of single blade based on NACA4412 airfoil.

关 键 词：浮式风力机 模型试验 翼型 FLUENT 升阻力计算 

分 类 号：TK83[动力工程及工程热物理—流体机械及工程]