Which equation represents the lift formula?

The lift formula is a fundamental equation in aerodynamics that describes the aerodynamic lift force generated by an aircraft's wings. The correct formulation of the lift equation is represented by the expression involving the coefficient of lift (C_L), air density (ρ), the square of the velocity (V^2), and the reference wing area (S).

In this context, lift is calculated using the equation:

Lift = C_L * (1/2) * ρ * V^2 * S.

This equation indicates that lift is directly proportional to the coefficient of lift, which is a dimensionless number that accounts for the lift characteristics of the wing shape and angle of attack. Air density and the square of the airspeed are also influencing factors; the lift increases with higher speeds and denser air, while it is also proportional to the size of the wing represented by the area (S).

Understanding this formula is crucial for pilots and aerodynamics engineers, as it provides insight into how to achieve and maintain sufficient lift for flight, especially when considering variations in speed, density, and wing design.