A two-dimensional numerical scheme for the compressible Euler equations is presented and applied here to the simulation of exemplary compressible vortical flows.The proposed approach allows to perform computations on ...A two-dimensional numerical scheme for the compressible Euler equations is presented and applied here to the simulation of exemplary compressible vortical flows.The proposed approach allows to perform computations on unstructured moving grids with adaptation,which is required to capture complex features of the flowfield.Grid adaptation is driven by suitable error indicators based on theMach number and by element-quality constraints as well.At the new time level,the computational grid is obtained by a suitable combination of grid smoothing,edge-swapping,grid refinement and de-refinement.The grid modifications-including topology modification due to edge-swapping or the insertion/deletion of a new grid node-are interpreted at the flow solver level as continuous(in time)deformations of suitably-defined node-centered finite volumes.The solution over the new grid is obtained without explicitly resorting to interpolation techniques,since the definition of suitable interface velocities allows one to determine the new solution by simple integration of the Arbitrary Lagrangian-Eulerian formulation of the flow equations.Numerical simulations of the steady oblique-shock problem,of the steady transonic flow and of the start-up unsteady flow around the NACA 0012 airfoil are presented to assess the scheme capabilities to describe these flows accurately.展开更多
文摘A two-dimensional numerical scheme for the compressible Euler equations is presented and applied here to the simulation of exemplary compressible vortical flows.The proposed approach allows to perform computations on unstructured moving grids with adaptation,which is required to capture complex features of the flowfield.Grid adaptation is driven by suitable error indicators based on theMach number and by element-quality constraints as well.At the new time level,the computational grid is obtained by a suitable combination of grid smoothing,edge-swapping,grid refinement and de-refinement.The grid modifications-including topology modification due to edge-swapping or the insertion/deletion of a new grid node-are interpreted at the flow solver level as continuous(in time)deformations of suitably-defined node-centered finite volumes.The solution over the new grid is obtained without explicitly resorting to interpolation techniques,since the definition of suitable interface velocities allows one to determine the new solution by simple integration of the Arbitrary Lagrangian-Eulerian formulation of the flow equations.Numerical simulations of the steady oblique-shock problem,of the steady transonic flow and of the start-up unsteady flow around the NACA 0012 airfoil are presented to assess the scheme capabilities to describe these flows accurately.
