Flow and Mechanical Characteristics of a Modified Naca Wing Geometry

Abstract

The flying ability is directly related to the structure of the wing geometry. The wing structure is designed differently according to each working conditions. In this study, a free-formed airfoil section was designed and the behaviour of the model under the influence of flow was investigated in terms of diving and takeoff angles. Computational fluid dynamics method was used in the analysis. The sensitivity of the method was checked by comparing the solution of a NACA airfoil section with the experimental results in the literature and its usability in the study was accepted. Also, in the study, the wing geometry was modelled as 3D and layered, and its mechanical properties were examined. The designed airfoil has more dominant flow structure in the lift direction. Non-symmetrical airfoil causes unsymmetrical Cl-Cd distribution. As a result of the wing structure being more dominant in lift, it was observed that the deformation and stress results of the positive angle of attack were higher than the negative results. Depending on the angle of attack, the pressure and flow effects on the wing caused a higher bending-torsion effect and increased the stresses in the fixation region of the wing. The lowest deformation and average stresses occurred at -4°a ngle of attack. The results are discussed as a result of flow and mechanical findings.