Abstract:
The report deals with the structural design and modal analysis of wing in an aircraft. Many studies are being carried out for the design of the wings across the globe by the researches to strengthen the aircraft wings for steady and sturdy structures for dynamic conditions. The wing design involves its initial considerations and selection of air foil, area of the wing, wing loading characteristic and weight of the wing. In this project the aircraft wing structures are designed using 2024-T3 aluminum alloy material. Airfoil profile NACA 63-215 as root of the wing and airfoil profile NACA 64-412 as the tip of the wing are selected (as per the specification of mooney M20n aircraft). The generated wing profile is imported to SOLIDWORKS 2017. Modal analysis is carried out in ANSYS WORKBENCH by inputting the specification of the wing geometry and the material properties. The reason behind using modal analysis is to determine the natural frequencies for vibration characteristics of the wing structure. Modal analysis also shows the correlation of the stress, deformation of the corresponding mode of vibration. The main purpose of this report is to compare natural frequency & deformation, structural properties (maximum principle stress, Von mises Stress, Von mises strain etc) of an aircraft wing with different thicknesses.
