Abstract
A numerical model for the calculation of incompressible viscous flows past airfoils and wings has been developed. The approach is based on a strong viscous-inviscid coupling of a boundary element method with the Navier-Stokes equations in vorticity-stream function formulation. A semiadaptive or fully adaptive grid is used. The interaction is achleved by iterative updating of the boundary conditions, through the wall transpiration concept. The Navier-Stokes equations are discretized on a semistaggered grid. Space-marching integration is performed starting from the stagnation streamline on two independent blocks. Results are presented for two different airfoils.
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