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Theory of Aerodynamic Coefficients

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Old   July 18, 2012, 16:12
Default Theory of Aerodynamic Coefficients
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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!
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Old   July 18, 2012, 21:34
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Have you tried xfoil?
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Old   July 18, 2012, 22:01
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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.
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Old   July 27, 2012, 03:35
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Thanks!! I could calculate with Xfoil tool
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