The aim of the research work describe in this paper was to model and simulate aerodynamic behaviour airfoil NACA 2410 completed with flap and slat using CFD. The work was also to distinguish between NACA 2410 using and without flap and slat in term of lift and drag coefficient quality. Simulation was carried out in various angles of attack. NACA 2410 was modelled by mean of design-Foil software and adjust the size geometry related to chord length within Auto Cad software that which would be converted into SolidWork to add flap and slat also angle of attack. Further simulation was undertaken in Ansys 14.5 by adjusting boundary condition. Parameters produced were coefficient of lift, drag, as well as pressure distribution and its velocity. The results showed that increasing angle of attack increased lift and drag coefficient. The use of flap and slat in the airfoil investigated produced much higher lift and drag coefficient. Maximum lift was achieved when airfoil set in 17° and 55° angle of attack without and with flap and slat, and flap deflexion angle of 30° as well as slat distance in x-direction of 4% from the chord in a slat angle of −2°.

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