MATLAB Assignment due tonight PB

Wing description ---------------- Unswept constant chord wing, span = 10, chord = 1, area = 10 alpha_0l = -2 deg throughout twist = 0 deg throughout 3 panels per half span alpha = 5 CAUTION! 3 panels per half span is way too less. It is used here solely to provide an easy test case for comparison. Also in this case the IC matrix is of size (6,6), so it is easy to display.

Use 50 panels per half span in the actual problems.

-------------------- My input file ------------ 0 % 0 for no symmetry, 1 for symmetry, 2 for sym+ige 10 % Sref 2 % npatch 1 % ipatch 3 % npan(ipatch) 0 -5 0 1 -2 0 % x y z c alfa0l twist 0 0 0 1 -2 0 % x y z c alfa0l twist 2 % ipatch 3 % npan(ipatch) 0 0 0 1 -2 0 % x y z c alfa0l twist 0 5 0 1 -2 0 % x y z c alfa0l twist 5 % alpha_deg -------------------- My output file ------------ IC (i.e., the [F] matrix) = -0.5622 0.0870 0.0147 0.0060 0.0033 0.0020 0.0870 -0.5622 0.0870 0.0147 0.0060 0.0033 0.0147 0.0870 -0.5622 0.0870 0.0147 0.0060 0.0060 0.0147 0.0870 -0.5622 0.0870 0.0147 0.0033 0.0060 0.0147 0.0870 -0.5622 0.0870 0.0020 0.0033 0.0060 0.0147 0.0870 -0.5622 rhs = -0.1219 -0.1219 -0.1219 -0.1219 -0.1219 -0.1219 IC_mid-point (i.e., the [F_m] matrix) = 0.1910 -0.0637 -0.0127 -0.0055 -0.0030 -0.0019 -0.0637 0.1910 -0.0637 -0.0127 -0.0055 -0.0030 -0.0127 -0.0637 0.1910 -0.0637 -0.0127 -0.0055 -0.0055 -0.0127 -0.0637 0.1910 -0.0637 -0.0127 -0.0030 -0.0055 -0.0127 -0.0637 0.1910 -0.0637 -0.0019 -0.0030 -0.0055 -0.0127 -0.0637 0.1910 wing_CL = 0.6323 wing_CDi = 0.0112