Numerical Study on Aerodynamic Characteristics of Wings of Passenger Aircraft under High Subsonic Conditions

In aerospace engineering, optimizing aerodynamic efficiency under high subsonic flight conditions is paramount. Traditional airfoil research and design methodologies have exhibited limitations, particularly in their efficacy at speeds approaching high subsonic speed, where drag reduction and lift enhancement become critical for performance optimization. These conventional approaches often fall short of addressing the nuanced aerodynamic challenges presented by high subsonic regimes. Addressing these limitations, the present research adopts a computational fluid dynamics (CFD) approach, utilizing ANSYS Fluent 2024 R1 to conduct a detailed numerical analysis of the NACA 0012 airfoil's performance. The study leverages Reynolds-averaged Navier-Stokes (RANS) equations to explore the aerodynamic characteristics of the airfoil, focusing on lift and drag behaviors and flow separation under various flight conditions. Therefore, this methodological framework enables a comprehensive evaluation of the airfoil’s aerodynamic efficiency in high subsonic flight. The findings reveal significant insights into the NACA 0012 airfoil’s aerodynamic properties, demonstrating its potential for drag reduction and lift optimization at critical flight speeds. Notably, the research elucidates the airfoil's ability to maintain aerodynamic stability and efficiency, highlighting its suitability for applications in modern aircraft designs aimed at high subsonic operations. The implications of this study extend beyond the specific aerodynamic performance of the NACA 0012 airfoil. By advancing the understanding of airfoil behavior in near-sonic conditions, this research can inform future airfoil design and optimization efforts, fostering the development of more efficient and environmentally sustainable aviation technologies.