|November 20, 2010, 09:41||
How to display Coefficient of lift (Cl)
Join Date: Nov 2010
Posts: 2Rep Power: 0
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.
|November 25, 2010, 09:09||
Join Date: May 2009
Posts: 90Rep Power: 6
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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