Abstarct: This study investigates turbulent flow over deformable airfoils with the aim of maintaining the desired lift coefficient. In order to achieve accurate results, the turbulence model (kω-sst) was used, which was selected due to its high accuracy in predicting turbulent behaviors around the airfoil. To simulate airfoil deformations, the C-type meshing method and the dynamic meshing method are used, which allow airfoil deformations without affecting the meshing accuracy. To ensure the accuracy of the results, this study uses NASA experimental data for the Naca 0012 and Naca 4412 airfoils as validation. The results obtained have been in acceptable agreement with the experimental data, and the accuracy of the methods used in this study has been taken into account. Also, comparison of the results of numerical simulations in dynamic mode with similar studies in the field of deformable airfoils indicates the success of numerical simulations in predicting the aerodynamic behavior of airfoils with different conditions. One of the innovative aspects of this research was the use of a proportional controller in the UDF coding to maintain the lift force at a constant value of 100 N and the lift force coefficient of 0/656. In this regard, the control coefficient K_p was optimized by the Ziegler-Nichols method and several analyses such as changing the angle, amplitude and frequency input were examined. The simulations showed that this option was optimized. Various were applied to the system. This research shows that by using proportional controllers and their precise determination, I can maintain the force on deformable airfoils in a stable manner. This is of particular importance in aerodynamic applications, especially where stability is required for optimal performance of flight systems.