Generation of a 2-D mesh around the airfoil. Faces around the airfoil used to control the density of the mesh. Mesh extents coincide with endplate dimensions. Faces extruded to form volumes.
Edge mesh to be applied in spanwise direction.
Wall' boundary condition to be applied to wing and endplate. Mesh applied to edges of outer domain. Nonconformal grid interfaces to be used. Tetrahedral mesh generated in domain. Boundary conditions then applied.