[Sandro23]

Hi,

I'm working on 3D CFD analysis of an airfoil and I compared the results obtained with several different codes.
That's my results for the aerodynamic coefficients :

mach = 0.10
alfa = 0

CL = 0.1357 (in-house code)
CL = 0.0548 (CFX)
CL = 0.0662 (Fluent)
CL = 0.1308 (XFLR5)

CM = -8.5438E-02 (in-house code)
CM = +2.2879E-02 (CFX)
CM = +3.3578E-02 (Fluent)
CM = -8.9100E-02 (XFLR5)

I don't understand why there is such a difference between Fluent's and Xflr5's results for an inviscid study.
I used the same mesh for the study with CFX and Fluent.
If someone can help me, it will be very appreciate. If you need more explanation, please ask me.

Regards,

Antoine.