The Kutta-Joukowski theorem quantifies the lift force generated by an airfoil. It states that the lift per unit span (\(L’\)) is directly proportional to the fluid density (\(\rho\)), the free-stream velocity (\(V\)), and the circulation (\(\Gamma\)) around the body: \(L’ = \rho V \Gamma\). This links the abstract concept of circulation to the physical force of lift.
