FREE VIBRATION ANALYSIS OF AN AIRCRAFT WING BY CONSIDERING AS A CANTILEVER BEAM

The present paper presents the modal analyses of a NACA 4415 airfoil profiled wing. Theoretical and numerical calculations are performed by considering the aircraft wing as a cantilever beam. The model is created and modal analyses are performed by using commercially available packages of SolidWorks and Ansys, respectively. The natural frequencies and the related mode shapes are obtained. The results of theoretical calculations are compared with the numerical modal analyses. The study has a conclusion that an aircraft wing can be considered as a cantilever beam that by ignoring the whole forces on the aircraft (except for gravity)