摘要
应用面元法的基本理论对风力机翼型气动求解方程进行推导,得出升力系数和阻力系数的表达式并在不同参数条件下对最大升力系数及最小阻力系数进行求解.研究表明,在最大升力系数作为目标函数且攻角变化时,减小翼型厚度;在最小阻力系数作为目标函数且攻角变化时,减小翼型的最大相对弯度并将翼型最大弯度的相对位置后移,才能使翼型的气动特性较理想.
Application of panel method the basic theory of wind aerodynamic wing type deduced by solving the equation,the lift coefficient and drag coefficient expressions and under different conditions in the maximum lift coefficient and the coefficient of least resistance to solve.Studies show that the maximum lift coefficient and angle of attack as the objective function changes,reducing the airfoil thickness;in the minimum drag coefficient as the objective function and the angle of attack changes,reduce the maximum relative curvature wing airfoil maximum curvature and the relative location shift,can better the aerodynamic characteristics of airfoils.
出处
《甘肃科学学报》
2010年第3期97-101,共5页
Journal of Gansu Sciences
关键词
面元法
风力机翼型
气动特性
升力系数
阻力系数
panel method
wind-wing type
aerodynamic characteristics
lift coefficient
drag coefficient
