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with a finite wing area of 60.0 m2 and an aspect ratio of 8. Assume the wing is composed of a NACA 65-210 airfoil with a span efficiency factor of 0.9. The measured profile drag coefficient is 0.012 for
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with a finite wing area of 60.0 m2 and an aspect ratio of 8. Assume the wing is composed of a NACA 65-210 airfoil with a span efficiency factor of 0.9. The measured profile drag coefficient is 0.012 for the entire aircraft. If the wing is at a 4 degree angle of attack, calculate CL and CD.

User Anttu
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The solution to the problem is given the attachments.

with a finite wing area of 60.0 m2 and an aspect ratio of 8. Assume the wing is composed-example-1
User Qerim Shahini
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