Examples of a centrally symmetric surface grid
at the leading edge of the ONERA M6 wing

Demonstration of a viscous flow solution of the FASTFLO CFD system;
Surface pressure distribution on the ONERA M6 wing-alone configuration
where centrally symmetric surface grid has been adopted

Demonstration of an inviscid flow calculation of the FASTFLO CFD system;
Surface pressure distribution for the AS28G wing-body-pylon-nacelle
computed on a three times adapted tetrahedral grid
(computed by SAAB in the FASTFLO project)

Demonstration of a viscous flow calculation of the FASTFLO CFD system; Surface
pressure distribution for the AS28G wing-body-pylon-nacelle computed on a hybrid
(prismatic/tetrahedral) grid having approximately 5.5 Mnodes

Technology demonstration of the FASTFLO CFD system;
Surface triangulation of a generic fighter configurations