Spatial adaption procedures on unstructured meshes for accurate unsteady aerodynamic flow computation

摘要: Spatial adaption procedures for the accurate and efficient solution of steady unsteady inviscid flow problems are described. The were developed implemented within a two-dimensional unstructured-grid upwind-type Euler code. These involve mesh enrichment coarsening to either add points in high gradient region or remove where they not needed, respectively, produce solutions spatial accuracy at minimal computational costs. A detailed description is given comparisons with alternative results experimental data presented provide an assessment efficiency capability. Steady transonic results, obtained using NACA 0012 airfoil, shown be accuracy, primarily that shock waves very sharply captured. savings factor approximately fifty-three case as much twenty-five cases.