The lift curve, which represents the coefficient of lift (Cl) against the angle of attack (α), passes through the origin for certain airfoils due to their specific geometric and aerodynamic characteristics. Airfoils with symmetrical shapes, such as the NACA 0012, exhibit this behavior because they generate no lift at zero angle of attack. Conversely, cambered airfoils, like the NACA 2412, produce lift even at zero angle of attack, resulting in a lift curve that does not intersect the origin. Understanding these distinctions is crucial for aerodynamic analysis and design.
PREREQUISITESAerospace engineers, students in aerodynamics courses, and anyone involved in the design and analysis of airfoil performance.