Problem 1: Given an elliptic wing whose chord is given by dy)=co1-(2y/bj2 Where c, is the wing root chord. The wing aspect ratio b/c, = 8. For AA a = 3 deg and a 2-0 = 0, by select three span positions 2 yg /b = 0.2, 0.5 and 0.8, you calculate the coefficients A. (n = 1, 2, 3) for the circulation based on the lifting line theory. Note: The system of algebraic equations for the coefficients A, in the Fourier series for the circulation distribution is [14]=[B] where 2b sin(nom). sinfnom) dom) sinoom B. = a + Qz-r 600m) You use the transformation y =- 2 +n cos(@) to convert 29, /6 to Bom (rad). The matrix for An is 6.0930 -2.8372 -6.7981 6.0930 -7.0930 0.0000 6.0930.-11.3487 12.6250 the solution for An is Al -0.008593506802788 A2 - 0 A3-0 Problem 1: Given an elliptic wing whose chord is given by dy)=co1-(2y/bj2 Where c, is the wing root chord. The wing aspect ratio b/c, = 8. For AA a = 3 deg and a 2-0 = 0, by select three span positions 2 yg /b = 0.2, 0.5 and 0.8, you calculate the coefficients A. (n = 1, 2, 3) for the circulation based on the lifting line theory. Note: The system of algebraic equations for the coefficients A, in the Fourier series for the circulation distribution is [14]=[B] where 2b sin(nom). sinfnom) dom) sinoom B. = a + Qz-r 600m) You use the transformation y =- 2 +n cos(@) to convert 29, /6 to Bom (rad). The matrix for An is 6.0930 -2.8372 -6.7981 6.0930 -7.0930 0.0000 6.0930.-11.3487 12.6250 the solution for An is Al -0.008593506802788 A2 - 0 A3-0