The NACA four-digit airfoils have the following camber distribution. z_c/c { = m/p² (2p x/c - (x/c)²) for x/c < p = m/ (1 * p)² (2p x/c - (x/c)²) for x/c > p. For the NACA 2412 airfoil the position of the maximum camber p=0.4 and the amount of maximum camber is m=0.02. Experimental data for this airfoil is attached. a) Use thin airfoil theory to determine the zero-lift angle of attack, α
zL. How does this value compare with the experimental data? b) Use thin airfoil theory to determine the moment coefficient about the aerodynamic center, C mac. How does this value compare with the experimental data?