Engine Boundary Conditions
 

I am attempting to model the influence of the engine nacelle on the wing of a Gulfstream G-II business jet. Does anyone know what boundary condition I should use for the inlet face and outlet face of the engine?

Currently, I have a pressure outlet boundary condition for the back of the flow volume, with velocity inlets for the other 5 faces.

Re: Engine Boundary Conditions
 

I should mention, I want to simulate the engine running, i.e. with a mass flow rate though the nacelle, if that makes sense...