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November 20, 2010, 08:41 |
How to display Coefficient of lift (Cl)
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#1 |
New Member
umar
Join Date: Nov 2010
Posts: 2
Rep Power: 0 |
Hi,
I am running Fluent and trying to calculate the lift coefficient for a symmetrical aerofoil. I want to compare the value of CL to the thin aerofoil theory, but i cannot seem to find out how to display the CL for AOA 2 degrees in fluent. Any help is much appreciated. Thank you |
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November 25, 2010, 08:09 |
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#2 |
Member
Burak
Join Date: May 2009
Posts: 90
Rep Power: 16 |
go to report-forces
select your airfoil (which must be a wall) select lift direction (ex: set y = 1) here you have the results. but dont forget to set reference values (velocity, area, etc.) |
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