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#1 |
New Member
Join Date: May 2013
Posts: 12
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I'm simulating an unsteady, low Mach number (M<0.1) flow. I also want to measure the generated sound.
I know that to find the sound caused by vortices I must enclose them by a "permeable surface" and define it as the sound source. This also means that I must use compressible simulations with the ideal gas law. The question remaining is whether I must reduce the time step to achieve a Currant number less then 1, even if the flow frequency is very small? Since I'm capturing the boundary layer, this will cause a time step 3 orders of magnitude smaller then the flow time scale. |
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#2 |
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Join Date: Mar 2014
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Hi! I'm trying to simulate jet noise in subsonic nozzles and I came across your post here.I would like to know how I can introduce an acoustic permeable surface in order to enclose the noise sources along my computational domain.I appreciate it if you could give me some guidance about it.
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#3 | |
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Jason
Join Date: May 2013
Location: South Africa
Posts: 32
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Tags |
compressibility, compressible flow, courant number, fluent 14 |
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