Full scale span load distribution on a tapered wing with split flaps of various spans

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Pressure-distribution tests were conducted in the full-scale wind tunnel on a 2:1 tapered U.S.A. 45 airfoil equipped with 20 percent chord split trailing-edge flaps of various spans. A special installation was employed in the tests utilizing a half-span airfoil mounted vertically above a reflection plane. The airfoil has a constant chord center section and rounded tips and is tapered in thickness from 18 percent c at the root to 9 percent c at the tip. The aerodynamic characteristics, given by the usual dimension less coefficients, are presented graphically as functions of flap span and angle of attack as well as … continued below

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[28] p. : ill.

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Parsons, John F. & Silverstein, Abe February 1937.

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This report is part of the collection entitled: National Advisory Committee for Aeronautics Collection and was provided by the UNT Libraries Government Documents Department to the UNT Digital Library, a digital repository hosted by the UNT Libraries. It has been viewed 485 times. More information about this report can be viewed below.

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  • Main Title: Full scale span load distribution on a tapered wing with split flaps of various spans
  • Series Title: NACA Technical Notes

Description

Pressure-distribution tests were conducted in the full-scale wind tunnel on a 2:1 tapered U.S.A. 45 airfoil equipped with 20 percent chord split trailing-edge flaps of various spans. A special installation was employed in the tests utilizing a half-span airfoil mounted vertically above a reflection plane. The airfoil has a constant chord center section and rounded tips and is tapered in thickness from 18 percent c at the root to 9 percent c at the tip. The aerodynamic characteristics, given by the usual dimension less coefficients, are presented graphically as functions of flap span and angle of attack as well as by semispan load diagrams. The results indicate, in general, that only a relatively small increase in the normal-force coefficient is to be expected by extending the flap span of an airfoil-flap combination, similar to the one tested, beyond 70 percent of the wing span.

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[28] p. : ill.

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  • Accession or Local Control No: 93R10691
  • OCLC: 1159597588
  • URL: http://hdl.handle.net/2060/19930081401 External Link
  • Report No.: NACA-TN-591
  • Center for AeroSpace Information Number: 19930081401
  • Archival Resource Key: ark:/67531/metadc54343

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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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  • February 1937

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  • Nov. 14, 2011, 10:28 p.m.

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  • July 16, 2020, 5:15 p.m.

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Parsons, John F. & Silverstein, Abe. Full scale span load distribution on a tapered wing with split flaps of various spans, report, February 1937; (https://digital.library.unt.edu/ark:/67531/metadc54343/: accessed April 25, 2024), University of North Texas Libraries, UNT Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.

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