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

The present work is a discussion of the computation of unsteady laminar incompressible two-dimensional viscous flow past complex geometries. A new physically consistent method is presented for the reconstruction of velocity fluxes which arise from the mass and momentum balance discrete equations. This closure method for fluxes makes possible the use of a cell-centered grid in which velocity and pressure unknowns share the same location while circumventing the occurrence of spurious pressure modes. The method is validated using the impulsively started cylinder problem for circular or aerofoil-like shapes at several Reynolds numbers of the order of 10(3)-10(4).