The applied numerical method is based on a two-dimensional incompressible Finite-Volume scheme to solve the Reynolds-averaged Navier-Stokes equations. The method is fully implicit and of second order in space and time. Based on the SIMPLE pressure correction algorithm, a co-located storage arrangement for all quantities is applied. Convective fluxes are approximated by a TVD-MUSCL-scheme.
The wind tunnel walls are considered as slip walls for the simulation. The computational domain starts 4 chords upstream and ends 8 chords downstream of the configuration.
The computational c-type mesh provides 202 chordwise cells around the
main airfoil and 196 around the flap resulting in 37,000 cells in
total. The non-dimensional wall-distance of the first cell center
remains below 
on the complete surface for an attached
steady case. Additional simulations use a 64,000 cells mesh to
evaluate the measure of mesh dependency.