(Aerospace) How to plot Lift Coefficient vs Angle of Attack

Hi. I'm studying aerospace engineering.

I want to plot Lift coefficient vs Angle of Attack Graph.

Unfortunately, I don't know how to approach the answer.

I know the 1 equation

Cl = 2pi[a + (1/pi) * {intergral 0 -> pi : (dz/dx)*(cos(theta) - 1) d(theta)}]

(where, 'a' is angle of attack, 'dz/dx' is camber function)

If we know the dzdx, we can plot the graph, right?

But I heard that this graph is (Re, AoA) function.

But I don't know how to apply Re...

Airfoil's type is not important.

Everything is OK(ex. NACA 0012 , NACA 2412. Actually we are finding this two airfoil Graph).

Please Help me. Please...... I don't have a lot of time. Thank you!