Hi. I'm working at drag and lift about an airfoil, but I can't found some information related to how to setup the area and depth in the 2D model. Clearly I can to see the area in a 3D model but must I to setup it by the nearest value? Thanks a lot if anyone can help me.

If the case is 2D, then the span of the airfoil is infinite. All values in Fluent are then calculated for a span of 1 unit. Therefore, if you have an airfoil with a chord length of 1 meter, Fluent will calculate forces and moments for a span of 1 meter and an area of 1 sq. meter.

Note, the 2D model does not include wingtip vortices for drag calculations

[smab]

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....

[Tushar K Herle]

What r the area, depth and length in those reference values??

[tobi1492]

hey guys,

I had the same problem 2 month ago. I fixed it in that way, that i calculate the drag and lift coefficient by myself.
cd = F_Drag / (p_dyn * A)

F_Drag can you calculate under Forces. pdyn is density / 2 * u.
For the area, you have to define any area you want. For example chord length * width or frontal area.

I hope this fixed your problem.

[dynamic]

Originally Posted by smab

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....

did you find a solution to this?