Theory of Aerodynamic Coefficients
 

Hello,

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! :)

Have you tried xfoil?

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.

Thanks!! I could calculate with Xfoil tool :D