一、引言在作者过去工作的基础上,本文提出在不计粘性时亚临界气流中给定翼型的几何形状和迎角求翼面的速度和压力分布的问题,以及给定压力分布设计翼型的几何形状并求对应的迎角的问题。关于不可压缩气流中的翼型压力分布已有许多计算方法,例如见参考文献[3]—[10]。作者在文献[1]中提出了一种近似方法,一方面比较简便,另一方面对通常实用翼型的相对 I. INTRODUCTION Based on the author’s past work, this paper presents the geometry of the airfoil in a subcritical airflow and the speed and pressure distribution of the airfoil at the angle of attack, and the design of the airfoil with given pressure distribution Geometry and seek the corresponding angle of attack. There are many computational methods for the distribution of airfoil pressure in incompressible gas streams, see, for example, Ref. [3] - [10]. In [1], the author proposed an approximation method, which is simple on the one hand, and on the other hand,