给出了一种基于欧拉方程的跨声速翼型设计方法。方法以Takanashi提出的“正反迭代余量修正”设计原理为基础，在气动力分析模块中，以欧拉方程为基本控制方程并采用Walz边界居方法对其进行粘性修正，反设计模块采用经过改进的二维翼型设计方法。方法的程序经过几个设计实例证明是有效而实用的。 A cross-velocity airfoil design method based on Euler’s equation is given. The method is based on the design principle of “positive and negative iterative margin correction” proposed by Takanashi. In the aerodynamic analysis module, the Euler equation is taken as the basic control equation and the Walz boundary method is adopted to correct the viscosity. The inverse design module adopts the modified Improved two-dimensional airfoil design method. The procedure of the method proved to be effective and practical after several design examples.