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本文提出了一种运用平面升力面理论来计算亚音速可压流中有限翼面上载荷分布的简易解法。运用了经典的理论公式来定义压力系数分布的函数。核函数的积分由一种称为闭型/有限和式的方法计算,从而得到一个性能良好的系数矩阵,这个系数矩阵和旋涡格网法中的相类似。使用本文方法可在计算中避免曼格勒型奇点。本文把升力及诱导阻力的弦向和展向积分推导为简单的和式,其项数和所用到的排列点的数目相等。分析结果分别与实验结果和其它方法的结果进行了比较,并说明了其收敛的快速性和计算效率。
This paper presents a simple solution to the problem of calculating the load distribution on a finite airfoil in subsonic subsurface compressors by using the plane lift surface theory. The classical theoretical formula is used to define the function of pressure coefficient distribution. The integral of the kernel is computed by a method called closed / finite sum, resulting in a well-behaved coefficient matrix similar to that of the spiral grid method. The method of this paper can avoid the Menger-type singularity in the calculation. In this paper, the chord and spread integrals of lift and induced resistance are derived as simple summation, the number of which is equal to the number of alignment points used. The results of the analysis are compared with the experimental results and the results of other methods, respectively. The convergence speed and computational efficiency are also illustrated.