[petr.f.]

Hi all,

I'd like to simulate flow over an airfoil (the standard NACA0012) with 2 degrees of freedom in OpenFOAM - as it is indicated on the attached picture. The result is investigation of aeroelastic stability with respect to various initial displacements, angles of attack and inlet velocities (please see other attached pictures). I do have my own inviscid solver and would like to compare it with OpenFOAM turbulent simulations. As for now, I've checked the wingMotion tutorial for pimpleFoam, but there are many unclear things for me (what is the exact physical model for aerofoil motion, how is the system of ODE describing this motion solved...).

I'd like to ask anyone for recommendations (or pointing to a right direction...) - e.g. is it necessary to re-program the sixDoFRigidBodyMotion solver or could I obtain the solution just by setting it up in a specific way?

Thanks a lot for any response