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I. Bögrekci, P. Demircioglu, H. Sucuoglu, E. Guven, N. Demir, M.N. Durakbasa:
"Structural and Modal Analyses of Naca 66-206 Aircraft Wing Model";
in: "Proceedings of the International Symposium for Production Research 2019, Lecture Notes in Mechanical Engineering (LNME)", 1; Springer Nature Switzerland AG, Cham, 2019, ISBN: 978-3-030-31342-5, 182 - 191.

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.

Lift and weight forces for aircraft wing Maximum deformation NACA 66-206 aircraft wing model Natural frequency Structural and modal analyses

http://dx.doi.org/10.1007/978-3-030-31343-2