The angle of attack plays a pivotal role in determining the performance of an aircraft wing, a critical component of its overall design. This angle, defined as the angle between the chord line of the wing and the relative wind direction, has a profound impact on the lift and drag forces experienced by the wing. When the angle of attack is low, the wing generates lift with minimal drag. However, at higher angles of attack, the wing encounters increased drag and may reach a stall condition.
Understanding the influence of the angle of attack on an aircraft wing is crucial in both design and operation, significantly impacting the aircraft’s capabilities in takeoff, climb, navigation, and landing. Therefore, a comprehensive comprehension of the relationship between the angle of attack and wing performance is imperative for ensuring safe and efficient aircraft operation. This study is dedicated to elucidating the effect of the angle of attack on aircraft performance, focusing on the variation in aerodynamic coefficients for two distinct airfoils. Employing Computational Fluid Dynamics (CFD) analysis via SolidWorks, the research examines NACA airfoil types, specifically NACA 2412 and NACA 4412, each featuring different cambers. The selected angles of attack for the investigation range from 0° to 20°, with a constant flow rate of 43 m/s. The findings reveal that the NACA 2412 airfoil exhibits a higher lift-to-drag ratio near to 20 compared to 6 in NACA 4412 airfoil. This insight provides valuable information for optimizing the aerodynamic performance of aircraft wings, contributing to the enhancement of overall efficiency and safety in aviation.