Clarky airfoil Fluent

kostas7 · May 12, 2014, 09:06

Hello to everyone,
I am currently new to this forum.I am a mechanical engineering student and i am workind with CFD simulation the past five months.
I am working on Clarky airfoil.I have made the geometry and the mesh process on Gambit and now i am trying to solve it on Fluent.What ever i have tried, it keeps showing to me reverse flow on pressure outlet and turbulent viscocity.
Does anyone knows exactly whats going on?Any help will be appreciated, since i am know a bit despaate!
Thanks in advance everyone!
Kostas

cfd seeker · May 14, 2014, 02:41

To solve the reserve flow problem, place the outlet of the domain far away from the airfoil.

Also I will suggest you to use Pressure farfield boundary condition at all boundaries of the domain. Place the INLET boundary at 5-7 chord lengths in front of airfoil, 5-7 times top and below and 15-20 times behind the airfoil.

Modify the turbulence parameters at the INLET boundary to have good starting solution for turbulence equations.

Also check your mesh quality, preferably use STRUCTURED mesh.

Hope it helps you.

May 12, 2014, 09:06	Clarky airfoil Fluent	#1
kostas7 New Member Konstantinos Dimoulas Join Date: May 2014 Posts: 2 Rep Power: 0	Hello to everyone, I am currently new to this forum.I am a mechanical engineering student and i am workind with CFD simulation the past five months. I am working on Clarky airfoil.I have made the geometry and the mesh process on Gambit and now i am trying to solve it on Fluent.What ever i have tried, it keeps showing to me reverse flow on pressure outlet and turbulent viscocity. Does anyone knows exactly whats going on?Any help will be appreciated, since i am know a bit despaate! Thanks in advance everyone! Kostas

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May 14, 2014, 02:41		#2
cfd seeker Senior Member Join Date: Mar 2011 Location: Germany Posts: 552 Rep Power: 20	To solve the reserve flow problem, place the outlet of the domain far away from the airfoil. Also I will suggest you to use Pressure farfield boundary condition at all boundaries of the domain. Place the INLET boundary at 5-7 chord lengths in front of airfoil, 5-7 times top and below and 15-20 times behind the airfoil. Modify the turbulence parameters at the INLET boundary to have good starting solution for turbulence equations. Also check your mesh quality, preferably use STRUCTURED mesh. Hope it helps you.