How to do blade element momentum theory analysis for different geometries of airfoil, e.g. NACA airfoils? I want to analyse NACA airfoils using BEMT. I have only yet done it for basic symmetric airfoils. I would like to know what all assumptions remain same in NACA airfoil analysis and to what degree it is accurate. Like for starters, will accounting for Cl-alpha change and geometrical changes in angle of attack be enough to analyse NACA airfoils?
The only difference would be the lift and drag coefficients used.  You'd need those to be specific to the airfoil(s) you choose.  Momentum theory is otherwise not sensitive to the airfoil shape.
Given the same lift and drag, momentum theory will give you the same induced velocity.