Consider a trapezoidal wing with no geometrical twist flying at 30ft/s and a span of 50 ft and a wing area of 312.5ft^2. The airfoil section has -o -1. The geometric angle of attack is 3. Assume the circulation distribution along the wing can be approximated by a sine series N r(0)=2bVA, sin no with A1=0.014247, A2=0, A3=0.000851, A4=0, A5=0.000615, A6=0 and A7=-0.000024. a. b. Write out the equation of the circulation [ as a function of (y--b/2 cose) Calculate the 3D lift coefficient C. Find the corresponding 3D lift curve slope (3D) d. Calculate the span efficiency factor e. The induced drag coefficient