Name
Abstract | ||
|---|---|---|
A nonet-Cartesian grid method, based on anisotropic/isotropic refinement, is presented for solving the Euler equations in gas dynamic problems. Grids are generated automatically, by the recursive subdivision of a single cell into nine subcells for isotropic nonet-Cartesian grids and into three subcells independently in each direction for anisotropic nonet-Cartesian grids, encompassing the entire flow domain. The grid generation method is applied here to steady inviscid shock flow computation. A finite difference formulation for the Euler equation using nonet-Cartesian grids is used to treat complex two-dimensional configuration. Results using this approach are shown to be competitive with other methods. Further, it is demonstrated that this method provides a simple and accurate procedure for solving flow problems involving multielement airfoils. |
Year | DOI | Venue |
|---|---|---|
2004 | 10.1023/B:JOMP.0000025931.79444.99 | J. Sci. Comput. |
Keywords | Field | DocType |
isotropic nonet-cartesian grid,grid generation method,shock flow computations,anisotropic nonet-cartesian grid,entire flow domain,boundary condition.,nonet-cartesian grid,cartesian grid,anisotropic,flow problem,shock wave,nonet-cartesian grid method,euler equation,isotropic refinement,inviscid flow,steady inviscid shock flow,finite difference,boundary condition,gas dynamics,grid generation | Inviscid flow,Isotropy,Mathematical optimization,Regular grid,Mathematical analysis,Finite difference,Grid method multiplication,Dynamic problem,Euler equations,Mesh generation,Mathematics | Journal |
Volume | Issue | ISSN |
20 | 3 | 1573-7691 |
Citations | PageRank | References |
0 | 0.34 | 3 |
Authors | ||
2 | ||