Scale-effect tests in a turbulent tunnel of the NACA 65(sub 3)-418, a = 1.0 airfoil section with 0.20-airfoil-chord split flap Page: 17 of 22
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4 0o . .8 2 /.6 20
Sect/on I/ft coefficien, oz
(g) Four-Foot-chorn rn odel/. = 2.24 I0 /vO M O. 08 .
F/gure 2.- Contnued.
Section lift coeff/ cie? c2
(h) Four-boo - chord mooel/. R 2.99 x/O' tv 0. 0.
Figure 2 . - Corluded.
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Tucker, Warren A. & Wallace, Arthur R. Scale-effect tests in a turbulent tunnel of the NACA 65(sub 3)-418, a = 1.0 airfoil section with 0.20-airfoil-chord split flap, report, September 1944; (https://digital.library.unt.edu/ark:/67531/metadc61404/m1/17/: accessed March 21, 2019), University of North Texas Libraries, Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.