Investigation of a Spoiler-Type Lateral Control System on a Wing with Full-Span Flaps in the Langley 19-Foot Pressure Tunnel

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Description

Tests of a partial-span model of a large bomber-type air1ane were conducted to determine the. aerodynamic characteristics of the wing equipped with full-span flaps and a retractable spoiler end aileron lateral control system. The arrangement consisted of (1) a double slotted flap extending over aproximate1y 86 percent of the wing semispan, (2) a 20-percent constant-percentage-chord aileron extending from the outboard end of the flap to the wing tip, and (3) a retractable spoiler, located at the 65-percent wing-chord station and extending from approximately 63 percent of the wing semispan to the wing tip. In addition, tests were made of a ... continued below

Creation Information

Deters, Owen J & Russell, Robert T August 1, 1947.

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  • Main Title: Investigation of a Spoiler-Type Lateral Control System on a Wing with Full-Span Flaps in the Langley 19-Foot Pressure Tunnel
  • Series Title: NACA Technical Notes

Description

Tests of a partial-span model of a large bomber-type air1ane
were conducted to determine the. aerodynamic characteristics of the
wing equipped with full-span flaps and a retractable spoiler end
aileron lateral control system. The arrangement consisted of
(1) a double slotted flap extending over aproximate1y 86 percent of the wing semispan, (2) a 20-percent constant-percentage-chord
aileron extending from the outboard end of the flap to the wing tip,
and (3) a retractable spoiler, located at the 65-percent wing-chord
station and extending from approximately 63 percent of the wing
semispan to the wing tip. In addition, tests were made of a wing
vent (of 1 and 2 percent of the wing chord located directly behind
the spoiler), perforations in the spoiler, a blot or cut-out along
the lower edge of the spoiler and spoilers of various spans.
With full-span flaps deflected and with the 2-percent vent open
or closed the initial stalling of the wing occurred at the tips, but
with the vents closed there probably would be no appreciable loss in
lateral control until maximum lift was reached. The l-percent vent
increased the rolling effectiveness of the spoiler at small spoi1er
deflections, particularly at high angles of attack with flaps
deflected. With flaps deflected the 2-percent vent caused a large
reduction in both the wing lift and rolling effectiveness of the
spoiler at large angles of attack. However, at small angle of attack
the 2-percent vent increased the rolling effectiveness of the spoiler at small spoiler deflections. The simultaneous operation of the
spoiler and vent (in contrast to a vent fixed in the wing) would result
in a large increase in the effectiveness of the spoiler and would
avoid any loss in wing lift as in a fixed vent arrangement.
The tests of the spoiler modifications revealed that (1) the
spoiler perforations reduced the rolling-moment and yawing-moment
coefficients but caused the spoiler hinge-moment coefficients to become more positive; (2) the spoiler slot had no notable effect on
the rolling-moment and yawing-moment characteristics but produced
a positive increase in the spoiler hinge-moment coefficients at
large spoiler deflections; (3) the effects produced by the individual
modifications were additive when the various modifications were
combined. In general, progressively decreasing the spoiler span by
removing the segments from the inboard end of the spoiler caused a
decrease in rolling effectiveness approximately proportional to the
span of the segment.

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Identifier

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  • : 93R11335
  • URL: http://hdl.handle.net/2060/19930082045 External Link
  • Report No.: NACA-TN-1409
  • Center for AeroSpace Information Number: 19930082045
  • Archival Resource Key: ark:/67531/metadc55487

Collections

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National Advisory Committee for Aeronautics Collection

The National Advisory Committee for Aeronautics (NACA) was a U.S. federal agency founded on March 3, 1915 to undertake, promote, and institutionalize aeronautical research. On October 1, 1958 the agency was dissolved, and its assets and personnel transferred to the newly created National Aeronautics and Space Administration (NASA).

Technical Report Archive and Image Library

This selection of materials from the Technical Report Archive and Image Library (TRAIL) includes hard-to-find reports published by various government agencies. The technical publications contain reports, images, and technical descriptions of research performed for U.S. government agencies. Topics range from mining, desalination, and radiation to broader physics, biology, and chemistry studies. Some reports include maps, foldouts, blueprints, and other oversize materials.

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Creation Date

  • August 1, 1947

Added to The UNT Digital Library

  • Nov. 14, 2011, 10:28 p.m.

Description Last Updated

  • Feb. 1, 2017, 5:47 p.m.

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Citations, Rights, Re-Use

Deters, Owen J & Russell, Robert T. Investigation of a Spoiler-Type Lateral Control System on a Wing with Full-Span Flaps in the Langley 19-Foot Pressure Tunnel, report, August 1, 1947; (digital.library.unt.edu/ark:/67531/metadc55487/: accessed October 19, 2017), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.