An investigation at Mach numbers of 1.40 and 1.59 of the effects of aileron profile on the aerodynamic characteristics of a complete model of a supersonic aircraft configuration

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

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Description

An investigation has been conducted in the Langley 4- by 4-foot supersonic tunnel at Mach numbers 1.40 and 1.59 to determine the effect of aileron profile on the aerodynamic characteristics of a complete model of a supersonic aircraft configuration. The model had a 40 degree sweptback tapered wing with 10-percent-thick circular-arc sections normal to the quarter-chord line. The ailerons were 20-percent chord and were located on the outboard 50 percent of the wing semispans. The various ailerons investigated included the basic circular-arc profile and three flat-sided ailerons having ratios of trailing-edge thickness to hinge-line thickness t of 0, 0.5, and ... continued below

Physical Description

40 p. : ill.

Creation Information

Spearman, M. Leroy & Webster, Robert A. January 15, 1951.

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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 30 times . More information about this report can be viewed below.

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  • Main Title: An investigation at Mach numbers of 1.40 and 1.59 of the effects of aileron profile on the aerodynamic characteristics of a complete model of a supersonic aircraft configuration
  • Series Title: NACA Research Memorandums

Description

An investigation has been conducted in the Langley 4- by 4-foot supersonic tunnel at Mach numbers 1.40 and 1.59 to determine the effect of aileron profile on the aerodynamic characteristics of a complete model of a supersonic aircraft configuration. The model had a 40 degree sweptback tapered wing with 10-percent-thick circular-arc sections normal to the quarter-chord line. The ailerons were 20-percent chord and were located on the outboard 50 percent of the wing semispans. The various ailerons investigated included the basic circular-arc profile and three flat-sided ailerons having ratios of trailing-edge thickness to hinge-line thickness t of 0, 0.5, and 1.0. Low aileron effectiveness was obtained with the circular-arc and t = 0 profiles. Increasing the trailing-edge thickness (t = 0.5 and 1.0) resulted in increased effectiveness as well as increased hinge moments with only a slight increase in drag.

Physical Description

40 p. : ill.

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  • Accession or Local Control No: 93R15738
  • URL: http://hdl.handle.net/2060/19930086448 External Link
  • Report No.: NACA-RM-L50J31
  • Center for AeroSpace Information Number: 19930086448
  • Archival Resource Key: ark:/67531/metadc58682

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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

  • January 15, 1951

Added to The UNT Digital Library

  • Nov. 16, 2011, 7:33 a.m.

Description Last Updated

  • April 13, 2018, 5:09 p.m.

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Spearman, M. Leroy & Webster, Robert A. An investigation at Mach numbers of 1.40 and 1.59 of the effects of aileron profile on the aerodynamic characteristics of a complete model of a supersonic aircraft configuration, report, January 15, 1951; (digital.library.unt.edu/ark:/67531/metadc58682/: accessed September 20, 2018), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.