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An elliptic grid-generation method for finite-difference computations about complex aerodynamic configurations is developed. A zonal approach is used, which involves first making a coarse global grid filling the entire physical domain and then subdividing regions of that grid to make the individual zonal grids. The details of the grid-generation method are presented along with results of the present application, a wingbody configuration based on the F-16 fighter aircraft.

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Transonic flowfields about a low-aspect-ratio advanced technology wing have been computed using a viscous/inviscid zonal approach. The flowfield near the wing where viscous effects are important was solved using the "Reynolds-averaged Navier-Stokes equations" in "thin-layer" form. The Euler equations were used to determine the flowfield in regions away from the wing where viscous effects are insignificant. A zonal grid using an H-H topology was generated around the wing by first solving a set of Poisson's equations for the global grid. This grid was then subdivided into separate zones of viscous or inviscid flow as suggested by the flow physics. A series of flow cases were computed and compared with corresponding sets of experimental data. All cases showed good agreement with experiment in terms of the pressure field. Also, an encouraging correlation between computed separated surface flow and experimental oil flow was obtained.

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