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daxterss July 18, 2012 16:12

Theory of Aerodynamic Coefficients

I have simulated some the flow field around a NACA profile. I would like to compare Cl, Cd,Cn, Cm gotten with CFD with theoretical expression. I know a very interesting book "Theory of Wing Sections" to compare my results but I am wondering if there is a free software which you choose the profile, flow conditions (Mach, Reynolds and angle) and it calculates the aerodynamic coefficients.

Thanks in advance! :)

lava12005 July 18, 2012 21:34

Have you tried xfoil?

atmcfd July 18, 2012 22:01

Check out the NASA website for "Foilsim". They are updating it to a new version, but I believe the applet gives reasonable estimates for the airfoils based on experimental data.

daxterss July 27, 2012 03:35

Thanks!! I could calculate with Xfoil tool :D

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