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A finite wing with an area of 2.0 ft2, an aspect ratio of 7.0 and a...

A finite wing with an area of 2.0 ft2, an aspect ratio of 7.0 and a span efficiency factor of 0.96 is mounted in a wind tunnel where the test section flow velocity is 110 ft/s at standard sea-level conditions. When the wing is pitched to a = -20, no lift is measured. When the wing is pitched to a = 10.00, a lift of 20 lbs is measured. Determine the lift curve slope for the airfoil (i.e., the infinite wing).

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