Active flow control is a promising method to improve aircraft performance and to delay or avoid boundary layer separation. The present computational study introduces an approach to active flow control by means of steady blowing jets. A method for automatic mesh refinement and inlet boundary condition generation for a geometrical specification of the jets is used and evaluated. First a single jet on a flat plate is used to evolve the procedure for analyzing the phenomenon and for studying the flow structure. This method is utilized for the case on the wing profile afterwards. The main questions for the wing are the ability of jets (placed close to the trailing edge) to prevent flow separation at higher angles of attack, and their effect on aerodynamic forces. As the results show, some distance behind the jet a vortex will evolve, expanding and shifting in the spanwise direction downstream. For the wing the counteracting jet pairs create counter-rotating vortices in the same way. These vortices will increase the momentum mixing within the boundary layer, which will become more resistive to separation. The actuators are effective to prevent separation on the wing profile up to an angle of attack of a = 14? and decrease the separation bubble at a = 16?, but at larger angles the separated region is too large and the jet does not help. The computed improvements are rather small, the aerodynamic forces are not significantly modified and the stall angle remains the same as well. Grid convergent results were difficult to obtain using the automatic mesh refinement procedure even with a large number of grid points. Further studies should include comparisons on meshes with different topologies in order to be able to quantify the accuracy of the present method.