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February 14, 2011, 19:55 |
Cl-alpha, 3d airfoil problem.
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#1 |
New Member
Levon
Join Date: Feb 2011
Posts: 3
Rep Power: 15 |
I am trying to determine dCl/d(alpha) for a 3d airfoil however Cl is barely changing (0.38-0.42) as I vary alpha (0-10 degrees), any help?
I only need preliminary results so my mesh is fairly coarse. Thanks. |
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February 15, 2011, 03:07 |
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#2 |
Member
Join Date: Jul 2010
Posts: 38
Rep Power: 16 |
If you are reporting Cl from the monitors, are you sure your reference values are correct?
If that's not it, I'd try refining your mesh first. |
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February 15, 2011, 10:29 |
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#3 |
New Member
Levon
Join Date: Feb 2011
Posts: 3
Rep Power: 15 |
My reference values are good, Fluent is simply underestimating the force produced by the airfoil as it changes angles. I also forgot to mention that my first mesh refinement did not fix the problem.
I am very closely following the 2D wing tutorials, at this point my wing is just a 2D airfoil that has been extruded. |
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Tags |
airfoil, alpha, angle of attack |
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