The mcl of both the NACA 4412 and the NACA 4424 is given by 

2 = b (b, + bz (2) - (2) 

where bo = 0.25, b2 = 0.0, b2 = 0.8, for 0.0 ≤ x/c, ≤ 0.4 

and bo = 0.111, b1 = 0.2, b2 = 0.8, for 0.4 ≤ x/c .≤ 1.0 

Find ci(α), cmac, αi=0, and Xcp/c (@α =3). Compare these results from thin airfoil theory (TAT) to the experimental data from Theory of Wing Sections for both airfoils. Comment on which airfoil is more accurately represented by TAT.