Hi @mgrandi, I actually did one of these last week. Firstly setup your mesh with an inlet-outlet condition, this allows you to alter the AOA iteratively without changing the mesh.

I set up a MATLAB file that produces values at the different angle of attacks with different velocities. since the aerofoil is symmetric in your case running with an AoA between 0 and 25 will give a nice curve. The data you need is the velocity, lift direction and drag directing in vertical and horizontal components.

Run a simulation for AoA of 0 degrees. You will need to define a forces coefficient result control. Duplicate the simulation and change the velocity, and lift/drag direction components at say 2 degrees AoA. Keep doing this until you have the lift and drag coefficients at the various AoA’s and then input the data to Matlab (or Excel) to plot your various graphs.

I’ll post my graphs when I get home and pop the link here.

Kind regards,

Darren Lynch