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Problem with airflow over naca0012 and angle o f attack

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Old   February 17, 2011, 14:27
Default Problem with airflow over naca0012 and angle o f attack
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Lucas Vieira
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Hello,

I'm working on a comparison between FA and CFX with some airfoils. I'm working with laminar flow Reynolds number of 360,000 for naca 0012. CFX simulates the data as followed. Now I'm trying to simulate in the OF, but the values of Cd and Cl are very different from those obtained in CFX and literature, and an angle of attack of 2 degrees the pressure field is completely irregular, I'm changing the angle of attack from speed change. Attached is the photo of the pressure field and cases.

naca0012_0.jpg

naca0012_1.jpg

naca0012_2.jpg

CFX:
CFX.jpg









Openfoam cases:

http://www.mediafire.com/?bgdmx03updfgckd

Thank you.
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Old   February 17, 2011, 14:50
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Felix L.
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Hello, Lucas,


with a Reynolds number of 360,000 the flow is expected to be turbulent, not laminar! A turbulence model would be appropriate to improve the numerical results, especially drag.

Another thing: the freestream boundaries are much too close to the airfoil surface. The distance between airfoil and farfield boundaries should be at least 20 cord lengths! Otherwise the flow close to the airfoil surface is distorted by the farfield boundary conditions and the results are negatively affected.


Greetings,
Felix.
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Old   February 18, 2011, 14:13
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Lucas Vieira
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Hello FelixL,
thanks for your reply.

I was wondering, why this problem did not show up in CFX, OF is much more sensitive than CFX? Because the pressure field for an 3 is completely different from the 2.

Other thing i am not sure if my case is set up correctly, now i am trying to
use the airfoild2d tutorial case, can you help me with the reference length and area for that airfoil.

Thanks,
Lucas Vieira.
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