A finite wing area of 1.5 ft2 and aspect ratio of 6 is tested in a...

A finite wing area of 1.5 ft2 and aspect ratio of 6 is tested in a subsonic wind tunnel at a velocity of 190 ft/s at standard sea-level conditions. At an angle of attack of ?1°, the measured lift and drag are 0 and 0.181 lb, respectively. At an angle of attack of 2°, the lift and drag are measured as 5.0 and 0.23 lb, respectively. Calculate the span efficiency factor and the infinite-wing lift slope. (Round the final answers to four decimal places.)

1) The span efficiency factor, e, is ________ .

2) The infinite-wing lift slope is _______ per degree.

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samet mamat answered 2 years ago

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