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NACA 23020 airfoil drag and lift calculation.

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Old   December 23, 2008, 10:24
Default NACA 23020 airfoil drag and lift calculation.
  #1
Zmur
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Hello everyone! I'm trying to calculate lift and drag for NACA 23020 airfoil using ANSYS Workbench, but I can't get correct results. Is there some kind of a guideline for this? Thank you in advance.
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Old   December 23, 2008, 17:27
Default Re: NACA 23020 airfoil drag and lift calculation.
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Glenn Horrocks
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Hi,

This question is asked so much we should write a FAQ on it... Any takers?

The CFX documentation has a good guide for getting accurate results. That's definitely a good place to start.

All these parameters need to be taken care of for a good result: * Simulation physics matching reality * Domain large enough to not affect results * Mesh quality acceptable * Mesh resolution OK * Converged * If transient, time step size is OK

Glenn Horrocks
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Old   December 23, 2008, 17:35
Default Re: NACA 23020 airfoil drag and lift calculation.
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Zmur
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Thanks. I'll look more thoroughly through the documentation.
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