[Torque_Converter]

In general I have created performance maps instead of trying to gather data for direct use in specific application. But right now I am at a position where I have no volume/mass flow rate data I can use or decide on, just a fan and its geometry.
I do know that it is pulling from atmosphere, and pushing to atmosphere pressure almost immediately after exit (blowing through battery case).
Right now the B.C.'s I've chosen are total stagnation perssure inlet=0 and entrainment outlet at P=0. I don't know if this is approrpiate since total pressure inlet should include a velocity term and this only drops to 0 some large distance from the inlet. And the need for entrainment at the exit is because there is some recirculation between the widely spaced blades.
What are boundary conditions appropriate to use here to determine the flow rate and thrust load resultant when no flow rate at a face is provided? Static pressure at either end is not robust even with zero gradient choices.