COMPUTATION OF UNSTEADY LAMINAR VISCOUS-FLOW PAST AN AEROFOIL USING THE CPI METHOD

The present work is a discussion of the computation of unsteady lamina r incompressible two-dimensional viscous flow past complex geometries. A new physically consistent method is presented for the reconstructio n of velocity fluxes which arise from the mass and momentum balance di screte equations. This closure method for fluxes makes possible the us e of a cell-centered grid in which velocity and pressure unknowns shar e the same location while circumventing the occurrence of spurious pre ssure modes. The method is validated using the impulsively started cyl inder problem for circular or aerofoil-like shapes at several Reynolds numbers of the order of 10(3)-10(4).