跨声速机翼的设计计算方法

THE COMPUTATIONAL METHOD FOR THE TRANSONIC WING DESIGN

本文介绍一种三维跨声速机翼设计计算方法,它以跨声速小扰动理论为基础,以给定的压力分布与分析计算的压力分布之差作为目标函数,应用Green定理建立起目标函数与机翼剖面形状修改量的线性代数方程组,从而求解出翼剖面的修改量,加到原来机翼各剖面上,再用分析计算程序计算,经过多次的反复,就可以达到设计目标。本方法的特点是分析计算程序与设计程序相对独立,只作小量修改就可联合使用。本文介绍用此方法设计的两个算例,说明设计结果是好的,计算机时与其它方法相比是大大缩短了。

The computational method for the 3-D transonic wing design has been presented in this paper. This method is based on small disturbance theory of transonic flow. The differences between the speci-fied pressure distribution and the analysis calculating pressure distribution are considered as the objective function. The linear algeraic equations about the objective function and the modified quantity of the wing section shape has been established using Green theorem. From this, the modified quantities of the wing section shapes can be solved. This modi-fied quantities have been added to the originalwing sections so that a new wing has been formed. The pressure distribution for the new wing are calculated using the analysis program again. This procedure is repeated until the objective of the design is achieved. The feature of the method is that the analysis program and the design program can be independent relatively each other. If the two programs are used together, only small changes are made. The two sample cases are presented in this paper. It isshown that the results are good. Comparing with other design methods, the computational time are reduced a lot to meet engineering purposes.