<p>This article details aerodynamic optimization, an efficient morphing wing CFD analysis of NACA 4415 Aerodynamical methodology that is focused on mitigating boundary layer separation. It mostly consists of the formulation of the new design methodology. First, it includes the modeling of the aeronautical structure which is numerically Precise engineered on one and, experimental results of the literature were acquired on the other. All these comparisons were made for noticing some changes in the value of <Emphasis Type="BoldItalic">Cl</Emphasis> and <Emphasis Type="BoldItalic">Cd</Emphasis> which were modified A lot with the lift angle of curvature from 1° degree to 18° degrees and incidence angles of eleven positive degrees and seven negative degrees. A case study was performed on the 2D plane wing model.</p><p>In addition, the authors seek to use this technique in order to deliver an unprecedented approach that is likely to be more effective at cost, time, and risk. A simplified geometry is presented in which the profile is subdivided into two mechanisms, a fixed one and a controllable one which allows for the assumption of different angles. ANSYS FLUENT was used to solve the steady Navier–Stokes equations as well as the Spalart–Allmaras turbulence model with a Re of 2e⁵ on an additional refined structured mesh.</p><p>The results are satisfactory, closely aligning with experimental findings reported in the literature. Special emphasis is placed on the importance of mesh selection, a critical step in numerical simulation. The choice of an appropriate meshing method significantly influences the study of drag variations and overall performance. Utilizing advanced Computer-Aided Design (CAD) tools, the results demonstrate the success of the CFD approach. The findings confirm that the developed methods effectively replicate experimental observations, marking a significant step forward in aerodynamic optimization.</p> Graphical Abstract <p></p>