提高钝前缘翼型的跨音速压力分布计算方法的精度与效率对翼型设计十分重要。国内对跨音速小扰动势流方法进行了研究,但对M_∞>0.8的超临界情况尚未计算。国外文献[3]指出当M_∞>0.9时完全速势方程的一种方法失败了。 本文试图改进经典的小扰动势流方程,探索比较稳定的迭代方法和超松弛方法,以克服超临界流计算常常不易收敛的困难,使小扰动势流计算的应用范围扩大到更高的M The accuracy and efficiency of calculating the transonic pressure distribution of blunt leading edge airfoils are very important for airfoil design. The method of transonic small perturbation potential flow in China is studied in China, but the supercritical conditions of M_∞> 0.8 have not been calculated yet. Foreign literature [3] pointed out that when M_∞> 0.9, a method of complete velocity equation failed. In this paper, we try to improve the classic small perturbation potential flow equation and explore the more stable iterative method and over-relaxation method to overcome the difficulty of often difficult to converge in the calculation of supercritical flow, so that the application scope of small perturbation potential flow calculation can be expanded to higher M