Sufyan, Ali & Jubril R,
Cite As :
Sufyan, Ali & Jubril R, . (2024). Aircraft Wing Utilizing the NACA 63-412 Airfoil: Implications for Design and Material Optimization 10.1007/978-3-031-18996-8.
Abstract
This research focuses on the structural analysis and optimization of an aircraft wing using the NACA 63-412 airfoil profile. The wing's specific dimensions, as detailed in the provided diagrams, serve as the basis for our study. The chosen NACA 63-412 airfoil is characterized by a maximum thickness of 12% at 34.9% chord, with a maximum camber of 2.2% at 30% chord, which is optimal for achieving enhanced aerodynamic efficiency and lift characteristics in subsonic flight conditions.The study involves computational simulations to evaluate the structural integrity, stress distribution, and deformation under various loading conditions, including lift and drag forces during different flight maneuvers. Advanced materials such as composite laminates are considered for the wing construction to minimize weight while maximizing strength and fatigue resistance.Additionally, the research incorporates analysis to assess the airfoil's performance, focusing on optimizing stall characteristics. The integration of these analyses aims to propose design modifications that could further enhance the wing's performance and durability.Ultimately, this research intends to contribute to the development of more efficient and robust wing structures for modern aircraft, aligning with ongoing advancements in aerospace engineering materials and design methodologies.