Anaça 2412 airfoil (the same one we already saw in class in the example exercise) is being considered for the wing on a small general aviation aircraft that is being designed. based on the estimated aircraft weight and wing planform area, the sectional lift l' at cruise conditions is estimated to be 2800 n/m. assuming air at standard conditions, a cruise velocity of 60 m/s, an airfoil chord of 2 m, and using the experimental coefficients shown on the following page, estimate the following at cruise conditions: (a) angle of attack (b) drag force per unit span (c) moment per unit span about the aerodynamic center (d) power per unit span required to overcome the drag (e) circulation of the starting vortex (f) location of the aerodynamic center (note that both the moment about the aerodynamic center and about the 1/4-chord point are indicated in the plots).