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: 10 of 22
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8 g NACA ACR No. 14122
3. For flap deflections above 150, the slope of the
section lift curve decreased with increase in flap
4. The section profile-drag coefficient with flap
deflected remained almost constant with Reynolds number,
although the section profile-drag coefficient for the
plain airfoil decreased up to a Reynolds number of
about 0.8 x 106 and then remained nearly constant to
a Reynolds number of about 3.0 x 106.
5. The slope of the pitching-moment-coefficient
curve of the plain eirfoil became slightly more negative
with increase in Reynolds number. The pitching-moment-
coefficient slope for the airfoil with flap deflected
varied with lift coefficient in such a way that presen-
tation of the slopes was not practicable.
Langley Memorial Aeronautical Laboratory
National Advisory Committee For Aeronautics
Langley Field, Va.
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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/m1/10/: accessed March 18, 2019), University of North Texas Libraries, Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.