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介绍了多块网格技术与流场分区求解方法在翼吊式双发民机机体／动力装置一体化研究中的应用．数值求解Ｅｕｌｅｒ方程模拟复杂组合体绕流．采用边界展方程／Ｅｕｌｅｒ方程耦合迭代技术进行器面粘性修正．为保持Ｅｕｌｅｒ方程求解中计算网格固定，粘流／无粘流耦合迭代采用表面源模型．该方法对某民用飞机模型跨音速绕流流场进行了数值模拟，机翼表面计算压力分布与实验吻合良好．
This paper introduces the application of multi-grid technology and flow field partitioning method in the integrated research of airfoil dual civil aircraft body / power plant. Euler Equation Numerical Simulation of Flow Around Complex Combinations. Surface Boundary Equation / Euler Equation Coupling Iteration Technique for Viscous Surface Modification. In order to keep the computational grid fixed in the Euler equation, the surface source model is adopted for the viscous flow / non-viscous flow coupling iteration. The method is used to simulate the transonic flow field in a civil aircraft model. The calculated pressure distribution on the wing surface is in good agreement with the experiment.