In this paper we show a numerical procedure for computing the incompressible viscous flow about an airfoil with a slat and a flap. The full Navier-Stokes equations are discretized in the curvilinear coordinates, using the cell method. The generalized Quick method is incorporated to suppress the instability from the convective terms at higher Reynolds numbers. The Multi-Domain technique, which divides the whole computational domain into several subdomains, is used to calculate this flow problem

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... ith a complicated geometry. Each solution is connected at the domain boundary by a versatile interpolation method. This procedure has been applied to calculate the flow about a NACA4412 airfoil at high Reynolds number for various attack angles, which resulted in a good agreement with experiment. Furthermore, the flows around an airfoil with a slat and a flap were successfully calculated. The flow patterns around the airfoil and inside the narrow slat and flap gap, and the effect of a jet through the gap are made clear. These results also show reasonable aerodynamic coefficients up to the stall region for two cases of flap deflection angle : 0° and 40°.