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Viscous flow over naca0012 airfoil

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Old   July 11, 2013, 03:33
Question Viscous flow over naca0012 airfoil
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Sreekanth
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I am new to CFD and SU2. I had gone through the tutorials in the SU2 website.
I am trying to find the Cl and Cd for flow over NACA0012 airfoil (using the same mesh given in test cases for inv_naca0012) .
For angle of attack = 0 deg, i get
Cd= 0.019274
Cl= - 0.001625
The Cd value is significantly high compared to NACA report which is around Cd=0.006.

The configuration file is attached ( in txt format). Kindly tell me what are the mistakes I have done.
Attached Files
File Type: txt configNACA0012.txt (7.9 KB, 17 views)

Last edited by shsreekanth; July 15, 2013 at 13:34.
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Old   August 16, 2013, 01:48
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Francisco Palacios
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Hi,

To run a RANS problem you need an a-priori adapted grid in the boundary layer. You will find those grids in the TestCases/rans folder

Thanks for using SU2,
Best,
Francisco


Quote:
Originally Posted by shsreekanth View Post
I am new to CFD and SU2. I had gone through the tutorials in the SU2 website.
I am trying to find the Cl and Cd for flow over NACA0012 airfoil (using the same mesh given in test cases for inv_naca0012) .
For angle of attack = 0 deg, i get
Cd= 0.019274
Cl= - 0.001625
The Cd value is significantly high compared to NACA report which is around Cd=0.006.

The configuration file is attached ( in txt format). Kindly tell me what are the mistakes I have done.
fpalacios is offline   Reply With Quote

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