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August 5, 2013, 16:39 |
Pressure Oscilations NACA 0012 Transonic
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#1 |
Member
Join Date: Apr 2012
Posts: 71
Rep Power: 13 |
Good Afternoon
I'm simulating some NACA at transonic speeds and when I extract the pressure and pressure coefficients from the wall it's possible to visualize some fluctuations on the pressure plots. I tried to use first and second order squemes, with different courant numbers but the problem still there. In some subsonic simulations I can see this fluctuations too. Is there anyone who knows how to correct this fluctuations ? Some data of my simulation (transonic one) are: SST K-w Mach 0,8 Second order and first order upwind (tried them both) thanks. |
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August 6, 2013, 03:18 |
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#2 |
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Join Date: Feb 2011
Posts: 62
Rep Power: 15 |
Hello,
I have had the same problem, I could only diminish the magnitude of the oscillations, but could never get rid of it, by preparing a fine boundary layer grid. Did you also use Icem CFD and construct a block-structured mesh? |
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August 7, 2013, 09:23 |
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#3 |
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Join Date: Apr 2012
Posts: 71
Rep Power: 13 |
Yes I'm using ICEM CFD. And my mesh is structured.
The first cell is 0.0001 m from the airfoil wall. I checked the y+ and it is around 3 for the airfoil. What's your y+ ? |
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August 10, 2013, 20:00 |
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#4 |
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Join Date: Feb 2011
Posts: 62
Rep Power: 15 |
I solved my problem by setting the tri tolerance to 10E-7 from 10E-3 (Settings->Model->triangulation) My y+ value is around 1 because I am using enhanced wall treatment. It depends on the wall function.
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March 21, 2017, 00:59 |
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#5 |
New Member
shuaiG
Join Date: Mar 2017
Posts: 1
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so it is the mesh that matters at last? i mean the oscillation of pressure coefficient
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