Abstract:

Presented here is a computational procedure for generating a mesh system and solving the Euler equation for transonic flow around a wing body tail combination . In the first part, an algebraic procedure for the generation of boundary fitted grids about wing body tail configuration is presented. The two boundary technique based on the concept of transfinite interpolation is used. As an example, an O C type grid for a model of wing body tail configuration is generated. They are of good quality. Second, an explicit time marching finite volume procedure solves the flow equation. The numerical results are in good agreement with experimental data.

Key words: wing-body-tail configuration, algebraic grid generation, two-boundary technique, transonic flow, Euler equation