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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.
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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.

User Dinuka De Silva
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3 votes

Answer:

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

Step-by-step explanation:

Please look at the image for the explanation of the answer

Compute the total circulation around a symmetrical airfoil whose circulation distribution-example-1
User Jin Yong
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Answer:

Please see attachment for the computation.

Compute the total circulation around a symmetrical airfoil whose circulation distribution-example-1
Compute the total circulation around a symmetrical airfoil whose circulation distribution-example-2
User Tharindlaksh
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