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March 25, 2010, 07:05 |
CFD vs Experimetal Results for Aerofoil
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#1 |
New Member
owhelan
Join Date: Mar 2010
Posts: 3
Rep Power: 16 |
Hi, I'm comparing experimental results obtained for a NACA 0012 aerofoil in a wind tunnel with CFD results ran on Fluent.
The CFD model was a very simple 2D, steady time, incompressible model using k-epsilon and standard wall functions. BC's were a pressure inlet and outlet and symmetry on upper/lower surfaces or fluid domain. Despite the low inlet gauge pressure of 215pa, I'm getting pressure readings on the surface of the aerofoil that lead to pressure coefficients greater than +ve 1 on the pressure surface at 9 deg and 12 deg incidence. Can anyone explain why this may be happening? Is it a problem with the wall function? Thanks Osh |
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March 25, 2010, 09:12 |
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#2 |
New Member
Karatix
Join Date: Sep 2009
Posts: 22
Rep Power: 17 |
What CFD Package and mesh generator do you use?
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March 25, 2010, 09:15 |
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#3 |
New Member
owhelan
Join Date: Mar 2010
Posts: 3
Rep Power: 16 |
I an using GAMBIT to generate the mesh and FLUENT to run the simulation.
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March 25, 2010, 10:54 |
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#4 |
New Member
Karatix
Join Date: Sep 2009
Posts: 22
Rep Power: 17 |
Unfortuntately I am not using Gambit and Fluent anymore and cannot remember whether I had similar problems. I think I used a structured grid without a wall function. The turbulence model was Spalart Allmares and worked pretty well.
Have you got subsonic, transonic or supersonic flow? Does it have a great difference between the value and +1? |
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