A significant step towards routine viscous flow simulations around aircraft configurations using workstations is presented. The paper describes a method for the generation of hybrid prismatic/tetrahedral grids for complex 3-D geometries including multi-body domains and employs it for viscous flows around an aircraft. An Automatic Receding Method (ARM) is presented which treats narrow gaps in cases such as wing-engine configurations, as well as multi-element wings. The second development is a combined octree/advancing front method for the generation of the tetrahedra of the hybrid mesh. The method requires minimal user interaction to specify mesh parameters such as grid spacing and stretching.
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