I'm a complete newbie when it comes to OpenFOAM, and I would like to obtain aerodynamic performance stats of a NACA 0012 at an AoA of 6 degrees. Can anyone advise me as to what code I need to input and where, as well as plotting lift + drag coefficients and forces?
The force coefficients can be added using the file forceCoeffs in system folder. You can check the link below.
Changes need to be made to the controlDict file as well to add it as a runtime function. You can check the tutorial case for flow over airfoil at the below location in your PC.