Structural and Modal Analyses of Naca 66-206 Aircraft Wing Model

In this study, NACA 66-206 wing type was modelled and analysed to understand to mechanical behaviour under lift and weight forces. Structural and modal analyses were applied using Ansys Workbench Static Structural and Modal Analysis tools. Three different materials (aluminum 6061, carbon fiber and strong unidirectional epoxy glass) were selected for structure of the wings. The wings were created with three parts as airfoil, rib and spar. The affected forces were calculated and applied to the wings for three motion velocities as 10, 50 and 100 m/s. In the analyses; the lift forces were calculated by the buoyancy equation for the aircraft. The weight forces were also added to get more realistic results. The motion velocity and material effects to the structural strength of the wings were compared according to the results obtained from static and modal analyses. The maximum deformations were observed for the 100 m/s motion velocity with the values of 2.28 mm for aluminum, 0.16 mm for carbon fiber and 7.71 mm for epoxy glass. The similar effects of the motion velocity were found for the strains and equivalent stresses. It can be concluded from these results that it was better to manufacture the NACA 66-206 wings with the carbon fiber material as it had high natural frequency values and caused to lowest weight force.