There are a lot of links which give the shape of the airfoil for any given set of camber thickness, position and max. thickness values, but I would like to know if it is possible to get the Lift vs. Angle of attack graph, i.e., in turn lift curve slope, and also Cl/Cd values for every NACA airfoil specified.
Actually, I needed the values to begin the designing of a basic propeller blade for my project.
I have tried searching a lot. It would be really helpful if anyone could help me proceed.