For an untwisted rectangular wing with an aspect ratio AR, the fundamental equation of Lifting Line Theory takes the form: 2b (0) - -0 (0o) = ( + c(0o) sine) An sin neo. Here, the chord length c(00), the angle of attack a(00) and the angle of zero lift =0(00) remain constant across the span. (a) When (00) - =0(00) = 10 and AR-5, establish a system of linear equations to solve for the Fourier coefficients An. (b) Solve the linear systems using 00 = 2 N'N, for N > 10 The spanwise distribution of circulation for the same wing be approximated as r = 4bv [0.02340 sin 0 + 0.00268 sin 30 +0.0072 sin 50 + 0.00010 sin 70], where b is the span and V is the free-stream speed. Calculate the lift and induced drag coefficient. can