The lift equation describes the fundamental relationship between the lift force generated by an airfoil and various aerodynamic factors. It is mathematically represented as $$L = C_L \cdot \frac{1}{2} \rho V^2 A$$, where $$L$$ is lift, $$C_L$$ is the lift coefficient, $$\rho$$ is the air density, $$V$$ is the velocity of the airflow, and $$A$$ is the reference area. Understanding this equation helps in analyzing how changes in speed, air density, or wing shape affect the amount of lift produced by an aircraft.
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