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A finite wing with a NACA 23012 airfoil has an area of 20 m2 , an...

A finite wing with a NACA 23012 airfoil has an area of 20 m2 , an aspect ratio 5.85, and a span efficiency factor of 0.85. If the wing has a profile drag coefficient of 0.004 at 6° angle of attack, calculate CL and CD.

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