Aerodynamic characteristics at subsonic and transonic speeds of a 42.7 degree sweptback wing model having an aileron with finite trailing-edge thickness Page: 4 of 26
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NACA RM No. LSKO2 3
p mass density of air, slugs per cubic foot
V air velocity, feet per second
M average Mach number over span of model
MT tunnel reference Mach number
MI local Mach number
R Reynolds number
The rolling-moment data have been corrected in accordance with the
method of reference 2 for reflection-plane models. This correction is
for extremely low Mach numbers. No correction has been made for Mach
number effect. The correction applied was as follows:
03a = 0.8970 easured
- All data are presented about the wind axes.
* MODEL
The semispan wing model for these tests had a leading-edge
sweepback of 42.70, a taper ratio of 0.50, and an aspect ratio of 4.0;
other geometric characteristics are shown in figure 1. The wing, made
of steel with a polished surface, had a 10-percent-thick circular-arc
section normal to the 50-percent-chord line, had no dihedral, and was
mounted as a midwing (fig. 1). The polished-brass fuselage was semi-
circular in cross section and was bent to the contour of the bump. The
fuselage for the tests on the side wall of the tunnel was made of hardwood.
The 50-percent-span outboard aileron was attached to the wing with a
1
-inch-thick copper insert (fig. 1). This insert was bent to obtain the
32
required aileron deflection. The deflection was checked before and after
each test. The various aileron profiles investigated are shown in
figure 2. The aileron chord was 20 percent of the wing chord.
TEST TECBHNIJE
The tests were performed in the Langley high-speed 7- by 10-foot
a tunnel which is capable of reaching the choking Mach number. In order
to obtain transonic speeds in the tunnel, an application of the NACA
wing-flow method of testing was made (reference 3). This method of
testing at transonic speeds involves placing the model in the high-velocity
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Turner, Thomas R.; Lockwood, Vernard E. & Vogler, Raymond D. Aerodynamic characteristics at subsonic and transonic speeds of a 42.7 degree sweptback wing model having an aileron with finite trailing-edge thickness, report, January 12, 1949; (https://digital.library.unt.edu/ark:/67531/metadc57819/m1/4/: accessed April 19, 2024), University of North Texas Libraries, UNT Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.