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Abstract : |
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. These parameters are determined automatically via an octree. The final quality of the tetrahedral mesh is improved using an automatic partial remeshing technique. Viscous flow solutions around the High Speed Civil Transport (HSCT) aircraft are presented. Both, subsonic and supersonic cases are considered and comparisons are made with experiments. Reduction in computer resources has been substantial, which allowed the solutions to be generated on a workstation rather than a supercomputer., |
