Question

Kutta-Joukowski’s theorem is defined for

• A. lift per unit span on the airfoil
• B. drag per unit span on the airfoil
• C. moment per unit span on the airfoil
• D. thrust per unit span on the airfoil

Hint:

Lift = \(\rho V \Gamma\) per unit span, where \(\Gamma\) is the circulation.

Answer 1

The Correct Option is A

Kutta-Joukowski theorem gives the lift per unit span as a product of fluid density, circulation, and freestream velocity.