Abstarct: The general purpose of the research is to design and analyze the combined mechanism to control the aerodynamic forces around the airfoil in different flight conditions. Increasing the lift force in critical flight conditions and saving the airfoil from stalling, as well as increasing the drag force and producing negative lift force (in the opposite direction, downwards) in order to help the aircraft descend and land when necessary, among other goals This is the main research. The mechanism under discussion consists of a small wing (with a chord length ratio of 1 to 4 and 1 to 8 compared to the main airfoil's chord length) on the primary airfoil (Naca0015). This small wing is capable of moving along all three coordinate axes (x,y,z) and can be positioned at the correct location and distance on the main airfoil. The analyses performed under different modes and conditions have been done using the commercial software Ansys Fluent. We created an organized grid with 104,000 cells, considered the flow as steady and incompressible with a Reynolds number of one milion used the K-Epsilon turbulence model. Among the results of this research, it is possible to save the wing from stalling and increase the lift coefficient from 0/784 to 1/3613 by using the lift increase system of this combined mechanism in a flow with an angle of attack of 15 degrees around the airfoil, which in normal stalling mode This angle occurs, it also pointed out that in cases where there is a need to reduce the lift force and increase the drag force, the drag force increased from 0/012 to 0/2341 with the use of the lift-kill system of the combined mechanism. :