Structural and Stress Analysis of NACA0012 Wing Using SolidWorks

Abstract

The aircraft wing is a critical component that enables flight and enhances safety and stability. Its design and function are critical considerations in the overall performance and safety of an aircraft. This paper aims to focus on the design of the aircraft wing structure for its importance. SolidWorks-2018 program was used to model the system of the wing parts, which consists of seven ribs and two spars and airfoil NACA 0012 was used and aluminum alloy T7075 as a material for the structure of the aircraft wing and its surface. The generated loads were projected on it obtained using the Vortex Lattice method when dividing it into (8, 16 and 24) panels to extract the amount of stress, strain and deformation to which the wing is exposed. The analyses conducted on the proposed wing showed that the wing structure is acceptable in design because of its lightweight, weighing approximately 5556.98 grams, and safe, as the stress resulting from the numerical analysis under the influence of the aerodynamic force is less than the yield strength of the structural material.