高空长航时无人机高升阻比两段翼型设计研究

Investigation of the design methodology for the high lift-to-drag ratio two-element airfoil of the high altitude and long endurance UAV

针对某特定无人机的使用设计要求,在单段翼型设计研究的基础上,尝试了高升阻比低雷诺数两段翼型的设计方法的分析与研究。采用求解椭圆型方程加控制点约束条件的"椭圆-控制点切割法"完成了两段翼型外形的生成,并针对巡航构型的襟翼偏角对缝道参数进行了优化;应用MSES计算分析程序对所设计的两段翼型的气动特性进行了分析评估。计算结果表明:本文所设计的两段翼型的最大升力系数达到2.72,最大升阻比为158.71;与原始单段翼型相比,最大升力系数增大了74.35%,最大升阻比增大了28.64%。

According to the design requirements of a special UAV,the design and analysis of the high lift-to-drag ratio two-element airfoil with low Reynolds number is conducted based upon the earlier studies of the one-element airfoil design.The geometry of the two-element airfoil is generated with ellipse-control points cutting method,the slot parameters for the airfoil with the flap deflection under cruise condition are optimized.The MSES code is used in evaluating the aerodynamic performance of the designed two-element airfoil.The results indicate that the maximal lift coefficient and the lift-to-drag ratio of the designed two-element airfoil are 2.72 and 158.71,respectively,and show increases of 74.35% and 28.64%,respectively by comparing to the one-element airfoil.