How to display Coefficient of lift (Cl)

3g_nitro · November 20, 2010, 08:41

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

kdrbrk · November 25, 2010, 08:09

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.)

November 20, 2010, 08:41	How to display Coefficient of lift (Cl)	#1
3g_nitro 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		#2
kdrbrk 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.)