Abstract:

The chimera embedding technique is presented to generate the grids for the configuration of a wing with control surfaces. It divides the whole region into many subdomains according to the wing, the aileron or the flaps, the cuts of the wing and the ends of the aileron or the flaps. The Renolds averaged Navier Stokes equations and Johnson King turbulence model are used for every subregion with the finite volume method.Through couple iterating, the solution of the whole flow field is obtained by exchanging information between subregions. The result of the delta wing with control surfaces shows that the results of the present method are in agreement with the experiment data very well.

Key words: chimera grid, flap, aileron, Johnson King turbulence model