Modeling and Structural Analysis of Aircraft Wing with Different Materials using FEM
M. Dyuthi Priya1, R. Vijaya Prakash2, B. Purna Chandra Sekhar3
1M. Dyuthi Priya, PG Scholar, Department of Mechanical Engineering, University College of Engineering & Technology, Acharya Nagarjuna University, (Andhra Pradesh), India.
2Dr. R. Vijaya Prakash, Assistant Professor, Department of Mechanical Engineering, University College of Engineering & Technology, Acharya Nagarjuna University, (Andhra Pradesh), India.
3Dr. B. Purna Chandra Sekhar, Assistant Professor, Department of Mechanical Engineering, University College of Engineering & Technology, Acharya Nagarjuna University, (Andhra Pradesh), India.
Manuscript received on 16 June 2025 | First Revised Manuscript received on 19 July 2025 | Second Revised Manuscript received on 04 August 2025 | Manuscript Accepted on 15 August 2025 | Manuscript published on 30 August 2025 | PP: 1-8 | Volume-13 Issue-9, August 2025 | Retrieval Number: 100.1/ijese.A37901012122 | DOI: 10.35940/ijese.A3790.13090825
Open Access | Editorial and Publishing Policies | Cite | Zenodo | OJS | Indexing and Abstracting
© The Authors. Blue Eyes Intelligence Engineering and Sciences Publication (BEIESP). This is an open access article under the CC-BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/)
Abstract: Aircraft Wing structure consists of skin, ribs and spar sections. The spar carries flight loads and the weight of the wings while on the ground. Other structural and forming members, such as ribs, are attached to the spars with stressed skin. The wings are the most critical components for producing lift in an aircraft. The design of wings may vary according to the type of aircraft and its purpose. Experimental testing of wing structure is a more expensive and time-consuming process. In this project, the detailed design of an aircraft wing structure was created using CATIA V5 R20. Then, a structural analysis of the wing structure is conducted to determine the stresses within it. The stresses are estimated using the finite element approach with the help of ANSYS-14.5 to determine the Stresses, strains, shear stress, and total deformations of the structure using different materials, including Al6061, S2 Glass, and carbon epoxy. This analysis ultimately concludes that the suitable material for the aircraft wing is.
Keywords: Aircraft, Wings, Airfoil.
Scope of the Article: Mechanical Engineering and Applications