[david1702]

Hi everybody

I want to calculate the lift and drag coefficients of a NACA Profile. For that I made a 2D mesh in ICEM and run the calculation in CFX (saved as Fluent Mesh and automatically converted to 2.5 D mesh for CFX). In the CFD Post I have calculated the forces in X and Y direction, and with the angle of attack my drag and lift forces. My question is which area should I take to calculate the lift coefficient?. CFX caclulates the area of the Profile (2.5D Profile), but I've read that the area that I need is Chordlength* Span. This two values are different.

If somenoe can help me, I will be very thankfull

Best regads
David