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...
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