NACA 23020 airfoil drag and lift calculation.

December 23, 2008, 09:24

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.

December 23, 2008, 16:27

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

December 23, 2008, 16:35

Thanks. I'll look more thoroughly through the documentation.

December 23, 2008, 09:24	NACA 23020 airfoil drag and lift calculation.	#1
Zmur Guest Posts: n/a	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.

December 23, 2008, 16:27	Re: NACA 23020 airfoil drag and lift calculation.	#2
Glenn Horrocks Guest Posts: n/a	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

December 23, 2008, 16:35	Re: NACA 23020 airfoil drag and lift calculation.	#3
Zmur Guest Posts: n/a	Thanks. I'll look more thoroughly through the documentation.

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