1. 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=2bV [4, sin +4, sin 36] You may compare your results against the output of the Matlab code prandtl.m as we will explain in the class. 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. 2. Using the results from Problem 1-a above, compute the following: a) What would be the 3-D lift curve slope when the angle of attack Is expressed in radians? Note: The wing is untwisted, and the airfoils are symmetric. b) How does it compare with the 2-D lift curve slope of 2? c) How does it compare with the lift curve slope of an elliptically loaded wing?