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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.

Respuesta :

Answer:

Please see attachment for the computation.

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Answer:

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

Explanation:

Please look at the image for the explanation of the answer

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