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Old   April 5, 2012, 12:36
Default kkl-omega coefficients
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Hey All!

I'm doing 3D wing analysis using the kkl-omega turbulence model.
Does someone of you know how to calculate
kl
kt
omega
nut
and nuTilda ?

thanks in advance
Christian
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Old   June 6, 2012, 04:23
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Hi ChrisPro,

you calculate omega and k like you do for the komegaSST or komega model. The other kl, kt you can get the values by looking at the paper:
"A three equation Eddy-viscosity model for Reynolds-Averaged-Navier-Stokes simulations of transitional flow". Journal of Fluids Engineering 2008.
Good luck.
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Old   June 6, 2012, 05:29
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Hey!

Thanks for your reply! I already did it but for the others who have a look at this thread:

you can leave away k

kt is calculated like k in the other turbulence models:
T*u_inf = sqrt(2/3*kt) / U_inf

in freestream one can set kl to 0

nut = Cmü,std * kt/omega

omega is the same as in the kOmegaSST model

Cmü,std = 0.09


I discovered that you can leave out nuTilda as well. The results are the same, but the timesteps it takes to get the desired residual is a bit higher!

greets
Christian
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Old   June 6, 2012, 05:31
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You are welcome ChrisPro. I am also working with kklomega, but my problem is the y+ = 1 condition which is not easy to satisfy while keeping the grid size manageable.
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Old   June 6, 2012, 14:53
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that's true!

at the moment I simulate a case which runs since yesterday morning on a 24core machine... (and now its 8.53pm in my time zone )

What experienced have you made with the calculated Cl and Cd values?

With y+ = 6 I also got good residuals ( < e-06 ) but the values for Cl and Cd where much lower than expected.

greets
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Old   June 7, 2012, 04:03
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Hi ChrisPro,

for the moment I have no results yet, just began the struggle with the mesh to make it y+ conform without ending up with trillions of elements . I will share my findings when I have some data. I am also considering DES as it is less demanding meshwise.
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Old   February 13, 2014, 05:26
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Hi ChrisPro

I am also interested in kklomega transition model. I have validated it for 2D airfoil, but not successful with 3D complex wing, it also have convergence problem. Would you please show your fvScheme and BC setting? and what about your solver? steady solver or transient solver?

Thank you!

Best regards,
Ye
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Old   June 16, 2014, 11:37
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I really hope someone could help me.
I am trying to simulate a simple 2D airfoil with kkl omega model.
My bcs are for wall are:
nut=zeroGradient
omega=zero Gradient
kt=0
kl=0

My setting are:
U=50m/s
TI=1%
turbulent length scale=0.01m
So:
kt=0.375
omega=61.23
nut=0.00055

I have use a very low relaxation factors, but I do not obtain good results.
My mesh, runned with SA (nutSpaldingWallFunction) runs correctly:
maximum yplus=2 ( just at TE region). Minimum=0.1. Average = 0.3

https://drive.google.com/folderview?...VE&usp=sharing
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