Finite element analysis of transonic flows in cascades: importance of computational grids in improving accuracy and convergence
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2a Ax accuracy and convergence accuracy problem amount of artificial applied artificial viscosity distribution artificial viscosity parameter Ax q2 basic boundary conditions cascade of NACA choked flow coarse grid computational grid convected convergence characteristics discretization errors downstream e e e element interfaces elliptic employed equation 34 ficial viscosity finite difference FINITE ELEMENT ANALYSIS finite element grid finite element method flow configuration flow direction flows in cascades grid refinement grid shown iterations Kutta condition leading and trailing leading edge modeling NACA 0012 airfoils nodal points nodes number of elements numerical integration potential flows pressure coefficients procedure pseudo-time radial grid relaxation parameter requires shock capturing solutions shock fitting technique shock region shown in figure smearing solution of transonic sonic line stagger angle staggered cascade subsonic and supersonic subsonic flows supersonic elements supersonic pocket supersonic region trailing edge transonic flow problems uniform convergence upstream values of artificial velocity potential