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Consider an aircraft wing with an aspect ratio of 10 and a taper ratio of 0.5. The cross-section of the wing is an airfoil

 

Consider an aircraft wing with an aspect ratio of 10 and a taper ratio of 0.5. The cross-section of the wing is an airfoil with a lift slope of 0.1 deg- and zero-lift angle of attack of -1.3. At an angle of attack of 4, calculate: a) The lift coefficient b) The induced drag coefficient.

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