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本文采用嵌合体埋入技术，将主段翼型和襟翼分成两子域，对多段翼型的复杂构型进行了分区迭代求解；在有限体积离散的基础上，求解欧拉方程计算各子域流场的解，通过各流场的耦合迭代得到多段翼型绕流的解，典型的带３０％襟翼ＧＡ（Ｗ）－１翼型算例表明，该计算方法稳定，能较好地模拟多段翼型中主段翼型与襟翼交接处的复杂流动现象，计算结果与实验值有较好的一致性。
In this paper, chimera embedding technique is used to divide the main airfoils and flaps into two subdomains, and the complex configurations of the multi-section airfoils are partitioned and iteratively solved. On the basis of the finite volume discretization, Euler equations are calculated for each sub The solution of multi-section airfoil flow is obtained through the coupling iteration of each flow field. The typical example of GA (W) -1 airfoil with 30% flaps shows that this method is stable and can be better Simulating the complicated flow phenomenon of the main section airfoil and the flaps in multi-section airfoil, the calculated results are in good agreement with the experimental data.