A finite wing area of 1.5 ft2 and aspect ratio of 6 is tested ina subsonic wind tunnel at a velocity of 190 ft/s at standardsea-level conditions. At an angle of attack of ?1°, the measuredlift and drag are 0 and 0.181 lb, respectively. At an angle ofattack of 2°, the lift and drag are measured as 5.0 and 0.23 lb,respectively. Calculate the span efficiency factor and theinfinite-wing lift slope. (Round the final answers to four decimalplaces.)
1) The span efficiency factor, e, is ________ .
2) The infinite-wing lift slope is _______ per degree.
