# reference values - 2D airfoil model

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 August 17, 2000, 18:35 reference values - 2D airfoil model #1 ANDRES ORTIZ Guest   Posts: n/a 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.

 August 20, 2000, 18:24 Re: reference values - 2D airfoil model #2 Shane Gillis Guest   Posts: n/a 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.

 August 20, 2000, 18:25 Re: reference values - 2D airfoil model #3 Shane Gillis Guest   Posts: n/a Note, the 2D model does not include wingtip vortices for drag calculations

 November 24, 2011, 02:12 #4 New Member   Shibin Mohamed Join Date: Nov 2011 Posts: 8 Rep Power: 6 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....

 February 5, 2014, 11:37 Depth and length #5 New Member   Tushar K Herle Join Date: Jul 2013 Posts: 6 Rep Power: 5 What r the area, depth and length in those reference values??

 February 6, 2014, 10:15 #6 New Member   Deutschland Join Date: Dec 2013 Posts: 4 Rep Power: 4 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. Maze likes this.

April 1, 2015, 18:33
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Ronald Thompson
Join Date: Mar 2015
Location: Portland, Oregon, USA
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Quote:
 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?

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