Summary of Airfoil Data Page: 59 of 724
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NACA ACR No. L5CO5
CON FID INTIAL
show a progressive change in type of scale effect with
location of minimum pressure. The data of figure 43
show that the maximum lift coefficient for the NACA
63(420)-.22 airfoil continues to increase with Reynolds
number up to 'values of at least 26 x 10
Three-dimensional data.- No recent systematic
threedimensional wing da-ta obtained at high Reynolds
numbers are available, so that it is difficult to make
any comparison with the section data. When the maximum-
lift data for three-dimensional wings are compared with
section data, account should be taken of the span load
distribution over the wing. The predicted maximum lift
coefficient for the wing will be somewhat lower than
the maximum lift coefficients of the sections used because
of the nonuniformity of the spanwise distribution of lift
coefficient, The difference amounts to about 4 to 7 per-
cent for a rectangular wing with an aspect ratio of 6.
Maximum-lift data obtained from tests of a number of
wings and airplane models in the Langley 19-foot pressure
tunnel are presented in table II. Although section data
at the Reynolds numbers necessary to permit a detailed
comparison are not available, the maximum lift coefficient
for plain wings given in table II appears to be in general
agreement with values expected from section data. The
data for the airplane models are presented to indicate the
maximum lift coefficients obtained with various airfoils
and configurations.
Lift Characteristics of Rough Airfoils
Two-dimensional data.- Most recent airfoil tests,
esoecifaly of airfoils with -the thicker sections, have
included tests with roughened leading edge (references 1
and 49), and the available data are included in the
supplementary figures. The standard roughness selected
for 21k-inch-chord models consists of 0.011-inch
carborundum grains anplied to the airfoil surface at
the leading edge over a surface length of 0.0c measured
from the leading edge on both surfaces. The grains are
thinly spread to cover 5 to 10 percent of this area.
The effect on maximum lift coefficient of various
degrees- of roughness applied to the leading edge of the
NACA 63(20)-422 airfoil is shown in figure 23. TheC CONFIDENTIAL
553
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Stivers, Louis S.; Abbott, Ira H. & von Doenhoff, Albert E. Summary of Airfoil Data, report, March 1945; (https://digital.library.unt.edu/ark:/67531/metadc61319/m1/59/: accessed April 24, 2024), University of North Texas Libraries, UNT Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.