HazelNuts39---nice handwriting
since that relation is used by the United States, I knew it'd be right
there also be an assumption of infinite aspect ratio so vorticity circulation, would be a factor...that alone would account for some divergence from expected, also, there will be some finite measure of slip 'eta' and other Rn effects that would need to be accounted for, let's not forget 'tunnel wall error' of course many partial solutions to this aspect of the NS equation have been published which are helpful in CFD renderings ..of the problem the total problem is so difficult that with out the airfoil ordinates dc/alpha and dalpha/dM relations it would be untenable to precisely predict any composite airfoil characteristics with high accuracy...of course aerodynamics is an experimental science and not theoretical
... I mean, we can now make a pile of dog cr#p fly if we wanna