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本文将文献[1]提出的流线迭代法进一步应用于计算正交流线坐标系中有攻角时的二维跨音速绕流。用该算法计算了α=1°情况下的6％双圆弧翼型和NACA0012翼型,计算结果与实验数据符合较好。
In this paper, the streamline iteration method proposed in [1] is further applied to the calculation of two-dimensional transonic flow around an angle of attack in the orthogonal line coordinate system. The algorithm is used to calculate the 6% double arc airfoil and NACA0012 airfoil with α = 1 °. The calculated results are in good agreement with the experimental data.