What should be the reference area for a 2d Airfoil Analysis
I have an airfoil (2d) of chord length 1 meter. The length of the camber line is 1.06m. The cross sectional area (2d enclosed area) is 0.17 meters. What should I give as the reference area if fluent for getting the correct cl.
Thanks everyone in advance for your help. 
Most of the time Airfoils use the square of the chord length as the reference area
Sincerly Adrien 
Thanks You

I have my NACA 23015 airfoil(flow speed 36m/s) which has a chord length of 100mm, max thickness 15.05mm,...
after scaling the grid to metres...what should be the reference values for area, length and depth... i am unable to obtain correct values for Cl and Cd...please help its very urgent....:( 
Refrence Area
The reference area should be your chord length (after scaling) and leave the length and the depth with the default values.

Just want to add something.
Reference area is Length and depth. Since depth is taken as 1, therefore reference area for 2d airfoil is taken as c * 1 = Chord length 
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