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给出了用Euler方程对大展弦比翼身组合体绕流的数值模拟，将Kroll的求解欧拉方程的有限体积法，推广到求解机翼机身流动问题，基本思想是使用保角变换、代数变换和椭圆方程变换混合方法生成机翼机身贴体网格。计算中使用有限体积法对欧拉方程进行空间离散，采用Runge－Kutta显式多步法求解关于时间的离散方程。在机翼机身表面上满足法向动量关系式。并采用了当地时间步长、隐式残值光顺和焓阻尼等技术加快收敛速度。本文方法具有准确、高效的特点，并可灵活应用到复杂流场计算中。
The Euler equation is used to simulate the flow around the airfoil body with large aspect ratio. The finite volume method to solve Euler equation of Kroll is generalized to solve the flow problem of wing fuselage. The basic idea is to use conformal transformation, Algebraic Transformation and Elliptic Equation Transformation Hybrid Method to Generate Airplane Body Fitted Grid. In the calculation, Euler equations were discretized by finite volume method and Runge-Kutta explicit multistep method was used to solve the discrete equations about time. On the wing body surface to meet the normal momentum relationship. The local time steps, implicit salvage and enthalpy damping are used to speed up the convergence. This method is accurate and efficient, and can be flexibly applied to complex flow field calculation.