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Old   August 4, 2009, 01:13
Default NACA 0012 data
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Jules
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Hi

I need some help please. I am looking at analyzing NACA 0012 airfoil using Fluent for a range of M (subsonic, transonic and supersonic) and angle of attacks. I am looking for reliable data – I have the book the theory of wing sections as well as a paper on experimental data ‘A Critical Assessment of Wind Tunnel Results for the NACA0012 Airfoil’ . However, in both these cases the results are very hard to read from the graphs and I'm worried about accuracy, so I would like to know if there is any way that I can get the data in tabular form or just better readable. Sorry if this is a stupid request, but I need something reliable to compare my data to.
Thank you.
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Old   August 4, 2009, 05:52
Default 0012 airfoil data
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NAVEEN.K.M
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hi pixie

search this book in google, u wil find the results for naca 0012 airfoil case....

NPL 9615 and NACA 0012 :A Comparison of Aerodynamic Data BY "N. Gregory and P. G. Wilby Aerodynamics Division", NPL
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Old   August 5, 2009, 02:08
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Ahmed
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Quote:
Originally Posted by naveen View Post
hi pixie

search this book in google, u wil find the results for naca 0012 airfoil case....

NPL 9615 and NACA 0012 :A Comparison of Aerodynamic Data BY "N. Gregory and P. G. Wilby Aerodynamics Division", NPL
The following link might help, with the mesh included
http://www.aero.polimi.it/freecase/?...A_0012_airfoil
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Old   August 5, 2009, 04:01
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thanx guys
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