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Old   August 28, 2007, 20:15
Default Re: K-Epsilon for Vortex Shedding
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First of all thanks for your replies in guiding me above.

1. I have tried SST-kw and LowReke and it seems that SST-kw is giving me better results. Right now, I am only modelling 2D but will move to 3D once I get the hang of things. In your experience, in RANS 3D modelling what is the most suitable model that predict the forces and vortex shedding accurately? How far do you usually place your first grid on the wall?

2. As shown in tutorial, I patch some y-velocity on the second half of my domain to produce some perturbation to initiate vortex shedding and I did observe vortex shedding. Is this justifiable? Will the y-velocity affect the calculation of force?

3. This might sound like a stupid question but how do we perform a time average of the Cd and Cl to get the mean value in unsteady solver? How can I get the Vortex Shedding frequency?

Thanks once again.

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Old   August 29, 2007, 02:03
Default Re: K-Epsilon for Vortex Shedding
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Hi Sham,

1. I never seriously tried RANS in 3D for this specific problem, once I applied the low-Re omega-based RSM just to see the effects, and it seemed qualitatively close to LES (good vortical structure behind the cylinder, much more detailed then any other RANS model). But I did not run the simulation long enough to be able to draw a conclusion on forces. Although I must mention that the grid was almost dense enough to try LES on it...

2. The artificial triggering of physical phenomena is perfectly justifiable if the final result or the evolution are not influenced.

For example, in a gaseous mixture of methane and air, the velocity of the flame front is totally dependant on the energy of the initial impulse, and consequently the effects. For a simple spark, the flame front will move at several tens of meters per second (deflagration) and the pressure created will blow (only) the windows and doors of the kitchen (hopefully). But if the initiation is made using a blasting cap (hard to find one of those in a kitchen, but anyway), the flame front will move at hundreds of meters per second (detonation) and the pressure created will be sufficient to blow away the whole kitchen, and the neighbor's too!

Seriously now, for the vortex shedding phenomenon, a patched y-velocity will have an influence on the forces for maybe no more than a few time steps. You would understand the necessity of the patching process if you'd try to simulate the problem starting from perfectly uniform initial conditions (the time elapsed until vortex shedding occurs will be very long). Even in such conditions, the vortex shedding will still appear, even for a perfectly symmetrical grid, because of round-off errors.

3. The mean Cl is going to be 0 anyway, but for Cd, in the past I used an external program to calculate the mean value, if I wanted an exact value, or simply estimated it by eye. But you could probably use the signal processing capabilities of FLUENT (FFT). I don't know this for sure, it's just a suggestion. The vortex shedding frequency is quite easy: simply count the min or max values of Cl within a certain timeframe and scale it to 1 second, and that's it.

All the best,


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Old   August 29, 2007, 02:56
Default Re: K-Epsilon for Vortex Shedding
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It is always stimulating to see replies from you. Thanks a lot for your help and hope you do not mind should I need more help later in my research.

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Old   August 29, 2007, 15:16
Default Re: K-Epsilon for Nozzle flow saparation
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Hi Razvan, You can see my domain in two images (sorry for the poor quality), one is of the complete domain and the over is focoused on the nozzle outlet after the gradient adaptation.

I will increase the size of the domain as you suggest. How much can I coarsen the grid as I move away from the nozzle outlet?

Using the Rk-e model gives me a large area of high turbulent viscosity limited to 100000 along the symmetry line starting at the shock wave. Will this be resolved by the SST k-w model?

Thanks Eilon
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Old   August 30, 2007, 01:35
Default Re: K-Epsilon for Nozzle flow saparation
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Hi Eilon,

The mesh seems OK inside the nozzle. But outside, you can relax it with a 1.025(L) x 1.1(H) growth ratio.

R-ke, as all high-Re k-e models, suffers from this annoying problem, extremely high levels of TVR for certain flows. K-e models are adequate away from walls, outside the B-L, but near the wall, they tend to heavily overpredict the TKE production. Shock waves are also strong TKE sources, so these two effects superimposed generate extremely high levels of turbulence, which forces TVR to grow so much.

K-w models are excellent for wall-bounded flows, especially SST-kw, so I would expect that in its case TVR should not go over 5000.

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Old   September 4, 2007, 20:22
Default Re: K-Epsilon for Vortex Shedding
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You suggested earlier to use fully structured O-H grid (which is just a rectangular domain with a circle around the cylinder)instead of just O grid that I was using.

Could you tell me how does grid type can affect the simulation? Will it affect the convergence time or the accuracy of the results?

How do we justify using the periodic BC at the top and bottom of the domain?

Thanks once again.

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Old   November 17, 2009, 11:03
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Dear Razvan,

Obviously you are an exceedingly excellent expert on Fluent by reading your posts! I wonder if you are still visiting this forum. I encounter a problem with sst k-w and really want you to kindly give some help. Please drop me a line if you would like to give a help:

Thanks a lot !
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Old   November 18, 2009, 04:35
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Hi Razvan.

I am simulating a pitching airfoil.

first, I have carried out steady state runs. I have a hybrid mesh .At Re = 6 * 10^6 so that i could check the CFD results with Theory of wings ,abbott values for the CL and Cd. I used Steady state, implicit slover,I have run both K-E standard and realizable. Y+ between 40-60 with standard wall function.I checked grid independency, looked for monotonic convergence of velocity magnitude at a point int the domain.Cp values are similar at 0 deg. I cannot predict similar Cl and Cd values at angle of attack like 15 deg. I have used Turbulence intensity 0.5% and TVR 5 as the inlet conditions. I am not sure if these values are correct as they are for a wind tunnel. Can you please find where i am going wrong and suggest.

Now coming to the actual application. Hydrofoil propulsion. I have to run cases at reduced frequency 0.1-1 with varying amplitude at Re = 12000. I am using sliding mesh to oscillate the foil After going through the insightful communication going on in this thread I have come to learn K-E standard and realizable are more suitable for high Re and i must use s kw or SST kw, keeping the y+ values in the check for the low Re to capture flow separation correctly. I plan to choose 20th of the time period as a time step.

Can you suggest how can I Model this problem correctly.
What Turbulence intensity and TVR values must i give as input.
Please suggest if i have missed out any steps.
I have to calculate the time averaged values of Cl and Cd do you know how to do it. this question has been put before.


Last edited by Kappe; November 18, 2009 at 04:55.
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Old   August 25, 2012, 12:32
Default Reverse flow in pressure outlet.
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Hello ppl, i had a gr8 time & understand a lot going through the discussion!!
I want to mention Mr. Razvan u hav done a gr8 job,i hav learn a lot through your replies.

This is the problem:
I am studying supersonic internal flows in ducts as a part of designing isolators, i used rectangular box domain of size 80x80x960 mm with pressure inlet and pressure outlet on front n rear faces of the 3D simple square cross section duct. but the flow in duct is not easy as i thought as it involves shock wave boundary layer interactions(SWBLI) and corner flows n really a complex domain.!!

So i modeled the flow in fluent with above boundary conditions with values as follows:
Pressure inlet: 2026500 pa
Pressure Outlet:101325 pa
( pressure ratio of 20 produces flow with Mach 2.5)
Total temperature at both and outlet: 300K
Turbulence model : standard K-e model with standard wall treatment

i used a quadrant of duct with 40x40 mm cross section to save computational effort.

i made a major mistake in choosing turbulence model n steady solver which i realised after gone through the thread,

so i got this reverse flows in 20 or 30 faces in pressure outlet zone, n residuals not converging at all, which shoots high to 10e+1after converiging to 10e-2..

The height of first cell off the wall is 1e-5m based on literature i still guess its very small.. i dunno how to compute Y+??

Also the fluent document suggested to maintain operating pressure of 0 for supersonic compressible flows but when i set to 0 it simply throws error as floating point error!! so i set to default value of 101325 pa

I need to capture SWBLI as well as secondary corner flow

so help me to overcome this problem..
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Old   November 22, 2012, 09:26
Smile Help with premixed combustion model!
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Dear Razfan,

i have read your posts and i am impressed with your knowledge. i wonder if you can help me with this:

I am trying to simulate flame-vortex interaction in a swirl stabilized dump plane combustor, basically the effect of vortex shedding on the flame, using the premixed combustion model of fluent. I also try to deduce the frequency of the instabilities, which is equal to the acoustic longitudinal quarter wave mode of the combustor, to compare with the experiments.
The problem is that the wall temperature is not known to me, but both the mean temperature inside the combustor and the inlet velocity are known.
I have done two trials:
1- using the adiabatic premixed model, in which i don't need the wall temperature, and set the velocity inlet and pressure outlet boundary conditions at both combustor inlet and exit respectively, along with periodic boundary conditions in the span wise direction where only a quarter section of the combustor was used. I used DES with RKE model as submodel. The continuity equation doesnot converge easily, although i started from a RANS steady state solution.(pressure based with SIMPLE algorithm used).
2- using the non-adiabatic model, with the same set-up, but applying massflow inlet at the inlet, and idealgas for density, while applying no heat transfer at the walls, i note that the solution converge so easy without the need to start from steady state solution but the temperature keeps rising in the combustor and exceeds the adiabatic flame temperature and keeps going up!!

could you please advice which is the best combustion model to use? and if periodic boundary conditions are appropriate with DES or i shall solve the complete combustor? and what type of pressure i need to monitor if i want to capture the acoustics? is it the static pressure or the dynamic one?

Thanks for your help. it is greatly appreciated.
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Old   July 10, 2015, 21:13
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Hi Razvan
I am Zeeshan. I am doing work on fluent. I need your help. If yes, then will send you my problem and questions
Zeeshan Latf
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Old   September 18, 2015, 16:04
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Hi Razvan,

I am new to CFD and analyzing the wind flow around 2-D square cylinder. Since you know a lot about modeling can you please guide me with the problem I am facing.

Flow Re=100 (unsteady) and I have modeled it in ADINA. Computational domain is 8D upstream, up and below the body and 18.5D behind.

But I cannot see the vortex shedding?

Divye Malik
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