A Fast grid generation procedure named parabolic equation method for complex aircraft is developed. Grid is obtained by marching from body surface to outer boundary. Successful control of grid orthogonality on body is achieved by means of the introduction of algebraic grid prediction. A numerical algorithm based on a finite volume explicit scheme is employed for calculating transonic flow around a realistic aircraft configuration. Comparisons of the computational results with experimental data show very good agreement in terms of trends.

The explicit and implicit methods are employed in the numerical simulation of unsteady transonic NACA10012 airfoil flow,and comparison analyses have been made in the respects of computational results,efficiency,and sensitivity to grid quality.

A body-fitted orthogonal grid around complex configurations including wing,body,pylon and nacelle has been suc-cessfully generated by applying the multi-block grid technique and the method of solving elliptic and parabolic partial differential e-quations.The transonic flow field and aerodynamic characteristics of the advanced twin engine transport aircraft are also simulated numerically by using finite volume methods to solve the Euler equations with high efficiency,and the viscous effect of wing bound-ary layer is considered.Results of the calculation show that pylon and nacelle have significant effect on the supercritical wing aerody-namic characteristics.the numerical results are in good agreement with the experimental wing surface pressure distribution data.

This paper utilizes a series of analytical transformations to generate two-dimensional curvefitted, orthogonal meshes. The generated meshes can be regulated and controlled according to the variation of the flow parameters in the flow field so as to obtain the optimal grid distribution. As an example, taking unsteady transonic flows over oscillating NACA 0012 airfoil, the effects of transformation accuracy on computation accuracy of flow field, and how to control the grid generation corresponding with the variation of the flow parameters are analyzed in detail.The proceeding techniques have been applied to solve Euler equations with succes and the numerical results are satisfactory.