A wing has a planform area S of 200 ft and a total span b of 40 feet. The airfoils are symmetric all along the span. The airfoil has a 2-D lift curve slope of 2 per radian. The wing has a rectangular planform, and thus has zero taper. The wing is untwisted. a. Compute the lift coefficient CL and the drag coefficient Coi at an angle of attack of 4 degrees. Use two terms in the series expansion for circulation. r=26V [4, sin +4, sin 36] b. Repeat the above calculation, now with just one term I=2bV-Asino. Compare the lift drag coefficient CL and CD values to problem #2 above. c. Compare the results for drag coefficient from part (b) above with that for an elliptically loaded wing at this lift coefficient.