Consider a wing with a thin, Symmetrie airfoil section in a Mach 2 airflow at an angle of attack of 1.5°. Calculate the lift coefficient
(a) For the airfoil section.
(b) For the wing if it is a straight wing with an aspect ratio of 2.56.
(c) For the wing if it is swept at an angle of 60°, with an aspect ratio of 2.56 and a taper ratio of unity. [Note: These are approximately the characteristics of the wing for the BAC (English Electric) Lightning supersonic fighter designed and built in England during the 1960s.]
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