Lateral-control investigation at transonic speeds of retractable spoiler and plug-type spoiler-slot ailerons on a tapered 60 degree sweptback wing of aspect ratio 2 : transonic-bump method

One of 5,164 reports in the series: NACA Research Memorandums available on this site.

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Description

Report presenting an investigation utilizing the transonic-bump technique through a range of Mach numbers in the high-speed 7- by 10-foot tunnel to determine the lateral control characteristics of retractable spoiler and plug-type spoiler-slot ailerons. The wing had a sweepback of 60 degrees at the quarter-chord line, an aspect ratio of 2, a taper ratio of 0.6, and an NACA 65A006 airfoil section parallel to the free stream. The plug-type spoiler-slot aileron was found to be more effective in producing roll than the retractable spoiler aileron through the entire range of values tested.

Physical Description

19 p. : ill.

Creation Information

Hammond, Alexander D. & Watson, James M. August 8, 1952.

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This report is part of the collection entitled: National Advisory Committee for Aeronautics Collection and one other and was provided by UNT Libraries Government Documents Department to Digital Library, a digital repository hosted by the UNT Libraries. It has been viewed 23 times . More information about this report can be viewed below.

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  • Main Title: Lateral-control investigation at transonic speeds of retractable spoiler and plug-type spoiler-slot ailerons on a tapered 60 degree sweptback wing of aspect ratio 2 : transonic-bump method
  • Series Title: NACA Research Memorandums

Description

Report presenting an investigation utilizing the transonic-bump technique through a range of Mach numbers in the high-speed 7- by 10-foot tunnel to determine the lateral control characteristics of retractable spoiler and plug-type spoiler-slot ailerons. The wing had a sweepback of 60 degrees at the quarter-chord line, an aspect ratio of 2, a taper ratio of 0.6, and an NACA 65A006 airfoil section parallel to the free stream. The plug-type spoiler-slot aileron was found to be more effective in producing roll than the retractable spoiler aileron through the entire range of values tested.

Physical Description

19 p. : ill.

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  • Accession or Local Control No: 93R16422
  • URL: http://hdl.handle.net/2060/19930087132 External Link
  • Report No.: NACA-RM-L52F16
  • Center for AeroSpace Information Number: 19930087132
  • Archival Resource Key: ark:/67531/metadc59253

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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).

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Creation Date

  • August 8, 1952

Added to The UNT Digital Library

  • Nov. 17, 2011, 10:13 p.m.

Description Last Updated

  • May 8, 2018, 1:13 p.m.

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Hammond, Alexander D. & Watson, James M. Lateral-control investigation at transonic speeds of retractable spoiler and plug-type spoiler-slot ailerons on a tapered 60 degree sweptback wing of aspect ratio 2 : transonic-bump method, report, August 8, 1952; (digital.library.unt.edu/ark:/67531/metadc59253/: accessed September 20, 2018), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.