Pressure Distributions on Plug- and Semaphore-Type Spoiler Ailerons on a 35 Degree Sweptback Wing of Aspect Ratio 4, Taper Ratio 0.6, and NACA 65A006 Airfoil Section at High Subsonic Speeds Page: 4 of 57
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NACA RM LS4F08
ss semaphore spoiler
w wing
R rear spoiler surface
F front spoiler surface
MODEL AND APPARATUS
The sweptback semispan-wing model used in this investigation was
mounted vertically in the Langley high-speed 7- by 10-foot tunnel with
the ceiling serving as a reflection plane. (The height of the test
section is 7 feet.)
The geometric characteristics and dimensions of the wing and spoiler
configurations are presented in figures 1 and 2. The steel wing was
swept back 550 at the quarter-chord line, had an aspect ratio of 4, a
taper ratio of 0.6, NACA 65AOO6 airfoil sections ,parallel to the free
stream, and neither twist nor dihedral.
The center line of the plug-type spoiler coincided with the
70-percent wing-chord line and deflections were obtained by rotating
about the 60-percent wing-chord line (fig. 1). Pressure orifices were
located on the upper and lower edges as well as on the front and rear
faces of the spoiler at three spanwise stations. The positions of the
orifices on the spoiler faces are given for each station in table I.
The semaphore-type spoilers were located also along the 70-percent
wing-chord line although each segment was skewed 19.5 forward. (See
fig. 2(a).) Deflections of these spoilers were obtained by rotating
them about an axis in the plane of the wing chord and normal to the face
of each segment. Pressure orifices were located on the upper and lower
edges as well as on the front and rear faces of one segment at three
stations along its length (fig. 2(b)). The positions of the orifices on
the spoiler for each station are given in table II.
TESTS
The tests were made in the Langley high-speed 7- by 10-foot tunnel
through the Mach number range from 0.60 to 0.93.
The plug spoiler was tested at projections of O, -0.02c, -0.04c
(gap unsealed), and -0.04e (gap sealed) through a maximum angle-of-attack
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Hammond, Alexander D. & Hayes, William C., Jr. Pressure Distributions on Plug- and Semaphore-Type Spoiler Ailerons on a 35 Degree Sweptback Wing of Aspect Ratio 4, Taper Ratio 0.6, and NACA 65A006 Airfoil Section at High Subsonic Speeds, report, August 30, 1954; (https://digital.library.unt.edu/ark:/67531/metadc60410/m1/4/: accessed April 24, 2024), University of North Texas Libraries, UNT Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.