本文以文[1]为基础,研究了平板锐缘边条机翼亚音速气动特性的解析估算,导出了曲线前缘边条机翼气动特性的通用计算式,并可计算尖梢机翼的展向升力分布;所需的位流常数采用涡格面元法来确定。本文就多种机翼进行了计算,与实验结果的比较表明,本方法具有计算简单快速、计算结果具有实用精度的优点,可供初步设计与性能分析时使用。 Based on the paper [1], this paper studies the analytical calculation of aerosonic aerodynamic characteristics of slab sharp edges and derives the general formula of the aerodynamic characteristics of the curved front wing, and calculates the Show the lift distribution; the required flow constant using vortex lattice method to determine. In this paper, a variety of wing was calculated, and the experimental results show that the method has the advantages of simple and fast calculation, the calculation results with practical accuracy, for preliminary design and performance analysis.