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How to display Coefficient of lift (Cl)

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Old   November 20, 2010, 09:41
Default How to display Coefficient of lift (Cl)
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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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Old   November 25, 2010, 09:09
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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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