The NACA 4-digit series of airfoil sections is defined by a thickness 7, a maximum mean-line ordinate m and a chordwise position p for the mean-line maximum. All are expressed as fractions of the chord. The first digit is 100m, the second digit is 10p (not 100p) and the third and fourth digits are 1007. The mean line distribution is then given by Zc = (2px - x) x p Zc and the thickness distribution is given by - zt 57 (0.2969x-0.1260x 0.3516x + 0.2843 0.1015x4) where zc, Zt and x are all normalized by the chord. For a zero-thickness NACA four-digit airfoil, calculate the the aerodynamics character- istics (Ce, a Lo, xcp, C'mac).