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-   -   Looking for 3D wind tunnel airfoil(wing) experimental data for CFD validation (https://www.cfd-online.com/Forums/main/153828-looking-3d-wind-tunnel-airfoil-wing-experimental-data-cfd-validation.html)

lzlz June 4, 2015 09:41
Looking for 3D wind tunnel airfoil(wing) experimental data for CFD validation
 
Hi all,

Currently I need to model the 3D wing for lift and drag coefficient calculations. I need some 3D wind tunnel experimental data for the CFD validation so that I can feel more comfortable about my simulation data. Where could I find these 3D experimental data?

thanks!!!

agd June 4, 2015 12:53
Try googling "ONERA M6"

fluid23 June 4, 2015 14:26
As agd suggests, ONERA M6 is a good option. Here are some others that I have used in the past as well...

Weber, J. and Brebner, G.G., ‘Low Speed Tests on 45-deg Swept-Back Wings. Part 1: Pressure Measurements on Wings of Aspect Ratio 5,’ Aeronautical Research Council, RM-2882, London, England, UK, ©1958.

Hall, I.M. and Rogers, E.W.E, ‘Experiments with a Tapered Sweptback Wing of Warren 12 Planform at Mach Numbers between 0.6 and 1.6,’ Aeronautical Research Council, RM-3271, London, England, UK, ©1962



Kolbe. C.D. and Boltz, F.W., ‘The Forces and Pressure Distribution at Subsonic Speeds on a Plane Wing Having 45
° Sweepback, Aspect Ratio of 3, and a Taper Ratio of 0.5,’ NACA RM-451G31, National Advisory Committee for Aeronautics, ©1951.



Graham, R.R., ‘Low-Speed Characteristics of a 45° Sweptback Wing of Aspect Ratio 8 from Pressure Distribution and Force Tests at Reynolds Numbers from 1,500,000 to 4,800,000,’NACA RM-L51H13, National Advisory Committee for Aeronautics, ©1951.



McAlister, K.W. and Takahasi, R.K., ‘NACA 0015 Wing Pressure and Trailing Vortex
Mesurements,’ NASA TP 3151, National Aeronautics and Space Administration,. Washington, D.C., ©1991.


Jacobs, W., ‘Pressure-Distribution Measurements on Unyawed Swept-Back Wings,’ NACA TM 1164, National Advisory Committee for Aeronautics, Washington, D.C., ©1947.


Johnson, H.S. and Hagerman, J.R., ‘Wind-Tunnel Investigation at Low Speed of An Unswept Untapered Semispan Wing of Aspect Ratio 3.13 Equiped with Various 25-Percent-Chord Plain Flaps,’ NACA TN 2080, National Advisory Committee for Aeronautics, Washington, D.C., ©1950.

lzlz June 4, 2015 22:01
Quote:
Originally Posted by agd (Post 548916)
Try googling "ONERA M6"
thank u very much！

lzlz June 4, 2015 22:04
Quote:
Originally Posted by MBdonCFD (Post 548931)
As agd suggests, ONERA M6 is a good option. Here are some others that I have used in the past as well...

Weber, J. and Brebner, G.G., ‘Low Speed Tests on 45-deg Swept-Back Wings. Part 1: Pressure Measurements on Wings of Aspect Ratio 5,’ Aeronautical Research Council, RM-2882, London, England, UK, ©1958.

Hall, I.M. and Rogers, E.W.E, ‘Experiments with a Tapered Sweptback Wing of Warren 12 Planform at Mach Numbers between 0.6 and 1.6,’ Aeronautical Research Council, RM-3271, London, England, UK, ©1962



Kolbe. C.D. and Boltz, F.W., ‘The Forces and Pressure Distribution at Subsonic Speeds on a Plane Wing Having 45
° Sweepback, Aspect Ratio of 3, and a Taper Ratio of 0.5,’ NACA RM-451G31, National Advisory Committee for Aeronautics, ©1951.



Graham, R.R., ‘Low-Speed Characteristics of a 45° Sweptback Wing of Aspect Ratio 8 from Pressure Distribution and Force Tests at Reynolds Numbers from 1,500,000 to 4,800,000,’NACA RM-L51H13, National Advisory Committee for Aeronautics, ©1951.



McAlister, K.W. and Takahasi, R.K., ‘NACA 0015 Wing Pressure and Trailing Vortex
Mesurements,’ NASA TP 3151, National Aeronautics and Space Administration,. Washington, D.C., ©1991.


Jacobs, W., ‘Pressure-Distribution Measurements on Unyawed Swept-Back Wings,’ NACA TM 1164, National Advisory Committee for Aeronautics, Washington, D.C., ©1947.


Johnson, H.S. and Hagerman, J.R., ‘Wind-Tunnel Investigation at Low Speed of An Unswept Untapered Semispan Wing of Aspect Ratio 3.13 Equiped with Various 25-Percent-Chord Plain Flaps,’ NACA TN 2080, National Advisory Committee for Aeronautics, Washington, D.C., ©1950.
Thank you very much for your answer. It's very helpful!


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