During the 1920s and early 1930s, the NACA obtained wind tunnel data on different airfoils by testing finite wings with an aspect ratio of 6. These data were then "corrected" to obtain infinite-wing airfoil characteristics. Consider such a finite wing with an area and aspect ratio of 1.5 ft2 and 6, respectively, mounted in a wind tunnel where the test-section flow velocity is 100 ft/s at standard sea-level conditions. When the wing is pitched to α = −2°, no lift is measured. When the wing is pitched to α = 10°, a lift of 17.9 lb is measured. Calculate the lift slope for the airfoil (the infinite wing) if the span effectiveness factor is 0.95.
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