Lift Using Kutta-Joukowski Theorem Calculator

The Kutta-Joukowski Theorem states that the lift force on an airfoil is proportional to the air density ($\rho$), the freestream velocity ($V$), and the circulation ($\Gamma$) around the airfoil.

• $L$ is the lift force,
• $\rho$ is the air density,
• $V$ is the freestream velocity, and
• $\Gamma$ is the circulation around the airfoil.