Ramjet Intake Simulation
I am trying to simulate (Inviscid FLow) a Ramjet Intake. Please find the geometry and BC in the attached figure.
I used the following BC
I specified pressure at the outlet to get a normal shock in the constant area portion of the intake.
First i initialized with fully supersonic flow and specified static pressure at the outlet, but the outlet BC was not sensed, which the simulation resulted in fully supersonic flow.
So i initialized with fully subsonic flow and specified static pressure at the outlet, but the flow reversal at the outlet and the solution is not converging.
So what would be a good strategy to simulate this kind of problem in fluent.
you should'nt specify a far field in such close proximity to your region of interest, well that true of most Bc's. Remember at a BC your are fixing values and if this is close to large gradients then you specify one side of that field.
If you want to model a nacelle with a ramjet inside then if this were to be 3 metres long for example the far field should be a half elipse shape, nominally 60m in diameter.
create the free stream boundary in front and extend the outlet boundary.
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