A technique of three dimensional unstructured adaptive multigrid

A technique of three dimensional unstructured adaptive multigrid based on the boundary of the computational domain is presented. The procedure begins with an initial coarse mesh and enriches this mesh in regions of high solution gradient. New boundary nodes are added by using an initial very fine boundary mesh to reflect the underlying surface representation of the geometry. The meshes after refining are used as multigrids, and the unstructured multigrid method is adopted to improve the efficient of flow solving. The transonic flow around M6 wing is simulated by solving Euler equations, and it is demonstrated that the flow shock on the wing can be captured accurately, and the pressure coefficient distribution on the surface shows a good agreement with the experimental data.