5) The NACA 4412 airfoil has a mean camber line given by N C 0.25 [0.8-] x (0.111 [0.2 + 0.8 - (+)²] C For a Mach number of 0.68, x for 0-≤ 0.4 X for 0.4≤ ½-½ ≤1 C a. Calculate the lift coefficient for an angle of attack of 3° b. Calculate the drag coefficient for an angle of attack of 3° c. Calculate the moment coefficient about the quarter chord point for an angle of attack of 3° d. Calculate the zero lift angle of attack e. Calculate the lift slope f. Plot the lift curve