Question

Compute the total circulation around a symmetrical airfoil whose circulation distribution is given by eqn. 4.24. Then compute the sectional lift of the airfoil using the Kutta- Joukowski theorem.

Answer 1

The answer is γ(θ) = 2αVα((1+cosθ)/sinθ)

Step-by-step explanation:

Please look at the image for the explanation of the answer

Answer 2

Please see attachment for the computation.