摘要
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 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.
出处
《航空学报》
EI
CAS
CSCD
北大核心
1990年第7期A309-A314,共6页
Acta Aeronautica et Astronautica Sinica
关键词
升力面
亚音速流
机翼
数值计算
lifting surface, subsonic flow, numerical calculation.
