A finite wing of area 1.5 ft2 and aspect ratio of 6 is tested in a subsonic wind tunnel at a velocity of 130 at standard sea-level conditions. At an angle of attack of – 1°, the measured lift and drag are 0 and O.l8llb, respectively. At an angle of attack of2°, the lift and drag are measured as 5.0 and 0.23 , respectively. Calculate the span efficiency factor .and the infinite-wing lift slope.
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