3) Consider the mean camber line for a NACA airfoil is given by Ус m Ус (2px - x²) = m (1-p²) (12p+2px-x²) upstream of maximum camber downstream of maximum camber where m and p are maximum camber and distance from the leading edge with respect to chord, respectively. (30 points) a. Calculate the angle of attack at zero lift. b. The lift coefficient when a=5°. c. The moment coefficient about the quarter chord d. The location of the center of pressure in terms of xcp/c, when a=5°.