The Kutta Condition is a principle in aerodynamics that states that the flow of air around an airfoil must be smooth at the trailing edge, allowing for the generation of lift. This condition requires that the velocity of the airflow leaving the trailing edge is equal on both the upper and lower surfaces of the airfoil. This concept is crucial in understanding how lift is generated as it ensures that the circulation around the airfoil is properly defined, which is essential in circulation theory.
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