亚音速升力面理论的一种新解法

 本文提供了亚音速升力面理论的一种新解法,可求解亚音速流中有限翼展机翼的载荷分布。计算中采用传统的弦向级数和展向分条。证明了Mangler二重奇异积分可交换积分次序,从而使积分可解析地求出。对弦向积分的被积函数作多项式分段逼近,可使核函数的表达式成为封闭形式的有限和,导致性态很好的系数矩阵。计算结果与实验及其它方法的结果作了比较,并给出了计算效率。

A NEW METHOD FOR SUBSONIC LIFTING-SURFACE THEORY Chinese Helicopter Research and Development Institute

A new method based on lifting-surface theory is presented determining the load distributions on finite wings in subsonic flows. A spanwise strip together with a classical chordwise series are used. By exchanging the order of the Mangier-type doubly singular integral, as justified in this paper, is made in order to make the calculations analytical and simple. A segmented polynomial approximation for the integrand of the chordwise integral is deduced to evaluate the kernal function in a closed form finite-sum manner, resulting a well-behaved coefficient matrix. Aanalytical results are compared with experimental data and other methods; the computational efficiency is demonstrated.