International Research Journal of Engineering and Technology (IRJET) e-ISSN: 2395-0056 Volume: 08 Issue: 11 | Nov 2021 www.irjet.net p-ISSN: 2395-0072 © 2021, IRJET | Impact Factor value: 7.529 | ISO 9001:2008 Certified Journal | Page 1002 Structural Analysis of an Aircraft Wing with Aluminium Alloy and Carbon Fibre Reinforced Polymer using Finite Element Analysis S Siva Sai Krishna 1 , Nutakki Priyatham 2 1,2 Student, Department of Aerospace Engineering, Hindustan Institute of Technology and Science, Chennai, Tamil Nadu, India, 603103 ---------------------------------------------------------------------***---------------------------------------------------------------------- Abstract - This paper deals with the modelling of a commercial aircraft wing and analysing its structural behaviour when subjected to an external pressure load. The design process starts with the modelling of the internal framework of the wing whose dimensions are similar to an actual commercial aircraft like the Airbus A350. The result of this simulation produced the stress, strain and displacement values and also determined the factor of safety (FoS) of this wing which was around 1.5 on an average. The wing structure consists of 16 ribs with 3 spars, the front and rear spars are made of rectangular cross section beams while the mid spar is made of an I-section beam. Two types of materials – Aluminium Alloy 7075-T6 (SN) and carbon fibre reinforced polymer composite Hexcel AS4C (3000 Filaments) have been used for comparison and identification of the most suitable material. The airfoil shape used for the ribs is NACA 23015. The software used for modelling and finite element analysis is SOLIDWORKS 2020. Key Words: Aircraft wing, stress, strain, displacement, SOLIDWORKS. 1. INTRODUCTION Wing is the main component of aircraft that is responsible for the generation of lift. During the forward motion of the aircraft, the air flows over the wing and produces a pressure difference between the top and bottom surface of the wing and generates the lift to the aircraft. The pressure difference is caused due to the aerodynamic shape of the cross section of wing and is known as aerofoil. Other components of the aircraft like fuselage and empennage are also aerodynamically shaped to reduce the amount of drag produced [1]. The main objective of this research is to identify the most suitable alternative for the conventional aluminium used in aircraft wings. Therefore composites are taken into consideration and their physical properties are being compared with the aluminium alloy. 2. Problem statement Aircraft wings are built to withstand the extreme weather conditions that occur during flight and the turbulence that is created should not affect the performance of the wing. Hence material selection is an important parameter to be considered when designing an aircraft wing. Composites made of carbon fibre has the capacity to serve this purpose due to its high stiffness, high strength and less weight. 3. WING MODEL The wing structure modelled in this study has an aerofoil cross section NACA 23015. The internal structure of the wing consists of 16 ribs and 3 spars, the front and rear spars are made of rectangular cross section beams while the mid spar is made of an I-section beam [3]. Table -1: Dimensions Root chord length 13m Tip chord length 3.5m Thickness of rib 0.2m Length of front spar 31m Length of mid spar 30.6m Length of rear spar 30.2m Figure 1 Isometric view of wing The above Figure 1 shows the isometric view of the internal structure of the wing. 3 spars have been connected from wing root to wing tip.