NACA 0012 data

pixie · August 4, 2009, 00:13

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.

naveen · August 4, 2009, 04:52

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

Ahmed · August 5, 2009, 01:08

Quote:

Originally Posted by naveen

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

pixie · August 5, 2009, 03:01

thanx guys

August 4, 2009, 00:13	NACA 0012 data	#1
pixie New Member Jules Join Date: Jul 2009 Location: Sydney, Australia Posts: 9 Rep Power: 16	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.

August 4, 2009, 04:52	0012 airfoil data	#2
naveen Senior Member NAVEEN.K.M Join Date: Mar 2009 Location: Bangalore, Karnataka, india Posts: 114 Rep Power: 17	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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August 5, 2009, 03:01		#4
pixie New Member Jules Join Date: Jul 2009 Location: Sydney, Australia Posts: 9 Rep Power: 16	thanx guys