摘要
本文介绍一种计算带分离的大中层弦比、小后掠角机翼低速气动特性的近似方法。根据给定机翼的平面形状和几何迎角,按线化升力面理论算出升力和力矩沿展向分布的第一次近似值。再逆向应用升力面理论估算下洗流场,从而近似地得到各个削面的有效迎角。然后根据有效迎角及雷诺数,从翼型实验数据得到相应的升力和力矩分布的第二次近似值。如此反复迭代直至收敛为止。
In this paper, an approximate method is presented to compute low-speed aerodynamic characteristics of high-middle aspect ratio and low sweep angle wing with separation. For given plane forms and geometrical angles of attack wing, we use the linear lifting surface theory to compute the first value of spanwise lift and the moment distribution of wing, and we adversely apply the linear lifting surface theory to the computation of the downwash flow field. So we will gain effective angle of attack at each wing section.According to known effective angles of attack and Reynolds number, we will get the corresponding second value of spanwise lift and the moment distribution of wing from exprimental data of airfoil aerodynamic characteristics. Iteration is done again and again until convergence is reached.
关键词
机翼
低速特性
分离
气动力
wings, lew speed characteristics, separation, high-middle aspect ratio, low sweep angle
