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-   -   Viscous flow over naca0012 airfoil (http://www.cfd-online.com/Forums/su2/120626-viscous-flow-over-naca0012-airfoil.html)

shsreekanth July 11, 2013 03:33

Viscous flow over naca0012 airfoil
 
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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.

fpalacios August 16, 2013 01:48

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 (Post 439093)
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.



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