Lift and drag coefficients vs AoA graphs of a specific NACA profile

[fog37]

TL;DR

How the lift coefficient $C_L$ versus #AoA$curve and the drag coefficient$C_D$versus$AoA## curve are calculated for a specific NACA profile...

Hello,
I would like to understand know how the lift coefficient $C_L$ versus AoA curve and the drag coefficient $C_D$ versus AoA curve are determined for the various tabulated NACA profiles.

Are computer simulation run for the different profiles assuming a certain Reynolds' number? Or can the two curves, the lift coefficient $C_L$ versus $AoA$ curve and the drag coefficient $C_D$ versus $AoA$ curve, be calculated analytically for every profile?

Thank you.

 

[jrmichler]

If you REALLY want to know how lift and drag are calculated, get a copy of Theory of Wing Sections, by Abbott and Von Doenhoff. Read the first five chapters.

I bought my copy back in 1987, and it helped convince me that I did not want to design and build my own airplane.