摘要
以风力机翼型为对象,应用边界层理论建立翼型前缘的气流分离模型,探讨气流分离前后翼型表面压力场和速度场的变化规律。相对于传统的翼型反设计理论,提出一种新的集成的、直接的通用翼型型线设计理论。基于泛函分析方法以及翼型保角转换理论,通过选取任意一组特征参数,建立通用风力机翼型型线的集成数学模型并提出其表面粗糙度敏感性的研究方法。研究了通用风力机翼型型线前缘不同分离点以及雷诺数对其气动性能参数的影响,得到不同表面粗糙度下通用型线气动特性的变化规律。研究结果对高性能低粗糙度敏感性的风力机翼型系列设计提供了理论基础,拓宽了风力机翼型的设计思路和方法。
Based on the boundary layer theory,a separation model of the wind turbine airfoils was presented.The transformation of pressure and velocity field on the airfoil surface were discussed.Compared with the traditional inverse design method,one direct and integral method for airfoil design was presented.Using the function equation of general wind turbine airfoil profile,an integrated mathematical model was presented.The roughess sensitivity of the general wind airfoil was calculated.The relation between the separation position,different Re number and aerodynamic performance were investigated for the general wind airfoils.The results provide enough theoretical support for the design of good performance and low roughess sensitivity.The design method and theory for wind turbine airfoils are developed.
出处
《中国机械工程》
EI
CAS
CSCD
北大核心
2011年第13期1588-1590,1596,共4页
China Mechanical Engineering
基金
国家自然科学基金资助项目(50775227)
重庆市自然科学基金资助项目(2008BC3029)
关键词
风力机翼型
通用型线
泛函分析
分离点
粗糙度敏感性
wind turbine airfoil
general profile
function analysis
separation position
roughess sensitivity
