Compute the total circulation around a symmetrical airfoil whose circulation distribution is given by eqn. 4.24. Then compute th

Question

2 years ago

12

e sectional lift of the airfoil using the Kutta- Joukowski theorem.

2 answers:

liberstina [14] · Answer 1 · 2022-03-20T14:35:05+03:00

6 0

Answer:

Please see attachment for the computation.

Nikitich [7] · Answer 2 · 2022-03-20T15:55:19+03:00

6 0

Answer:

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

Explanation:

Please look at the image for the explanation of the answer