OpenFOAM case for simulating the flow over a NACA 2412 airfoil at 8 degrees angle of attack.
The airfoil is aligned with the x-axis, so it's the velocity components that control the angle of attack. The Spalart Allmaras turbulence model is used for this case.
This case is setup to be run using simpleFoam, the steady-state solver for incompressible, turbulent flow. Simply run the run.sh script to renumber the mesh and execute the simpleFoam solver.
If you'd like to experiment, you can use the clean.sh script to quickly clean the case directory. It will remove several directories and the log file.
To adjust the angle of attack, the velocity components must be modified in the 0/U dictionary, as well as both the lift and drag directions in the system/forceCoeffs dictionary.
The mesh can be located in the constant/polyMesh directory. The exported grid as well as the Pointwise project file are available. If you have Pointwise, you can open the naca2412.pw file and manipulate and/or regenerate the mesh.