The lift of an airfoil refers to the upward force generated by the airfoil when it interacts with a fluid flow, typically air. This force is perpendicular to the direction of the flow and is a result of the pressure difference between the upper and lower surfaces of the airfoil. Lift enables an aircraft to overcome gravity and stay aloft, making it a critical parameter in aerodynamics and aircraft design. The formula to calculate Lift of an airfoil as follows:
Where:
- Cl is the lift coefficient of an airfoil,
- q∞ is the Dynamic pressure in Pa,
- S is the Reference area in m2.