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Old   December 5, 2012, 04:27
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Robin Debroux
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Hi everybody!

I'm trying to simulate a subsonic flow in a nozzle.
I've tried to do this with rhoCentralFoam but the simulation didn't give good results. I don't know if it comes from my BC's or if rhoCentralFoam can't deal with subsonic flow.

I've attached my 0 folder to show you my BC's.

Thank you for your help.
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Old   December 5, 2012, 10:03
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Hello,

what do you mean when you say "no good results"? Donīt they reach a steady state or anything else?


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treima
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Old   December 5, 2012, 10:22
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After one iteration, I've got a Mach number of 0.43 but I know after analytical calculations that my maximum Mach number has to be more or less 0.1 at steady state.

Thank you!
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Old   December 5, 2012, 13:38
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Your case looks like its adapted from a 2D case. If this is what you want, then the frontAndBack boundaries should be of tpe "empty" for all your variables; in some of them they are "empty", in some they are "zeroGradient".
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Old   December 5, 2012, 14:18
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For a Mach number about 0.1, is it really necessary to use a compressible solver?
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Old   December 6, 2012, 05:46
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Quote:
Originally Posted by treima View Post
For a Mach number about 0.1, is it really necessary to use a compressible solver?
Yes, you're right. But what I would like to do is to test different solvers for different flows. I've already tested sonicFoam for a large range of Mach Number (subsonic to supersonic flows). It works good. And now I would like to test with rhoCentralFoam and compare the results.
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Old   December 6, 2012, 05:49
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Quote:
Originally Posted by mturcios777 View Post
Your case looks like its adapted from a 2D case. If this is what you want, then the frontAndBack boundaries should be of tpe "empty" for all your variables; in some of them they are "empty", in some they are "zeroGradient".
Yes, it's adapted from a 2D case. I'll test your boundaries and see what it gives.

Thank you for your advise.
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