Wind-tunnel investigation of effect of yaw on lateral-stability characteristics 3: symmetrically tapered wing at various positions on circular fuselage with and without a vertical tail Page: 4 of 25
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NACA Technical Note No. 825
The model (see fig. 1) was the same as the one used
for the tests of reference 4, except that the fuselage
was recut so that the wing could be mounted about 0.5 of
the mean chord forward and about 0.5 of the mean chord
rearward of the original position. For the high-wing and
the low-wing combinations the outer surface of the wing
was made tangent to the surface of the fuselage. In all
cases -the wing wad set at 00 incidence.
The 3:1 symmetrically tapered wing, which is fully
described in reference 3, is of NACA 23012 section with
the maximum upper surface ordinates in one plane, giving
the chord plane a dihedral of 1.450. The tips are formed
of quadrants of approximately similar ellipses. The
sweepback of the locus of one-quarter chord points is
4.750, the area is 4.1 square feet, and the aspect ratio
is .6.1.
The.fuselage is circular in cross section and was
made to the ordinates given in reference 8. The vertical
tail is of NACA 0009 section and has an arbitrary area of
53.7 inches, which includes a portion through the fuselage
as shown in figure 1. Its aspect ratio, based on this
area and the span measured from the center line of the
fuselage, is 2.2.
Split flaps af :20-percent chord and 60-percent span
were made of 1/16-inch steel. For the high-wing and the
miding combinations, the flaps were cut to allow for the
fuselage, and the gaps between the fuselage and the flaps
were sealed. . The flaps were attached at a 600 setting.
When the wing was in the low rearward position, a
fillet was used. The fillet is shown in figures 2(a) and
2(b).
TESTS
The test procedure was similar to that used in previ-
ous investigations (references 4 and 5). The wing was
tested in the high, the;middle, and the low positions at
0.5 of the mean chord both forward and rearward of the
longitudinal locations used in reference 4. Tests were
made with and without the flaps and with and without the
vertical tail for all wing positions.
All combinations were tested at angles of attack3
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Recant, Isidore G. & Wallace, Arthur R. Wind-tunnel investigation of effect of yaw on lateral-stability characteristics 3: symmetrically tapered wing at various positions on circular fuselage with and without a vertical tail, report, September 1941; (https://digital.library.unt.edu/ark:/67531/metadc54573/m1/4/: accessed April 23, 2024), University of North Texas Libraries, UNT Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.