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Old   June 23, 2008, 04:19
Default Lift calculation
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Hi Guys

I'm sticking to a problem, concerning the lift calculation of my CFX results.

The results I have is the static pressure on the upper and lower surface of the airfoil,the question is how to calculate the resulting force on that airfoil.

I've displayed the pressure plot on the 2 surfaces and exported it to excel and inserted the "trendline". then I integrated that curve so I got my resulting force. the problem is, that I don't rely on the "excel-way-of-calculation".

Is there another way to compute the force on my airfoil. I don't want to use the "force" data of my results, because I think they aren't right.


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Old   June 23, 2008, 06:37
Default Re: Lift calculation
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You should use the CEL expression for force:


Bu if you don't believe the force from CFX, the static pressure alone is not enough to calculate the lift force. You would also need to export face areas and components of the surface normals in order to calculate the force in a specific direction properly.
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