Consider a rectangular wing constructed with a NACA 2412 airfoil section, with efficiency e 1 (a) In a single graph, plot the lift coefficient as a function of angle of attack, from - to +12, for R- 16, 8, 12,20, oo) (b) In a single graph, plot the induced drag coefficient as a function of angle of attack, from -6o to +120, for R 6,8, 12,20, oo]. When plotting use MATLAB and include the code Consider a rectangular wing constructed with a NACA 2412 airfoil section, with efficiency e 1 (a) In a single graph, plot the lift coefficient as a function of angle of attack, from - to +12, for R- 16, 8, 12,20, oo) (b) In a single graph, plot the induced drag coefficient as a function of angle of attack, from -6o to +120, for R 6,8, 12,20, oo]. When plotting use MATLAB and include the code