The aerodynamic characteristics of a model wing having a split flap deflected downward and moved to the rear

One of 4,120 reports in the series: NACA Technical Notes available on this site.

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Description

From Summary: "Tests were made on a model wing with three different sized split trailing-edged flaps, in the NACA 7 by 10 foot wind tunnel. The flaps were formed of the lower rear portion of the wing and were rotated downward about axes at their front edges. The lift, drag, and center of pressure were measured with the axis in its original position and also with it moved back in even steps to the trailing edge of the main wing, giving in effect an increase in area. The split flaps when deflected about their original axis locations gave slightly higher ... continued below

Physical Description

7 p. : ill.

Creation Information

Weick, Fred E. & Harris, Thomas E. May 1932.

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

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  • Main Title: The aerodynamic characteristics of a model wing having a split flap deflected downward and moved to the rear
  • Series Title: NACA Technical Notes

Description

From Summary: "Tests were made on a model wing with three different sized split trailing-edged flaps, in the NACA 7 by 10 foot wind tunnel. The flaps were formed of the lower rear portion of the wing and were rotated downward about axes at their front edges. The lift, drag, and center of pressure were measured with the axis in its original position and also with it moved back in even steps to the trailing edge of the main wing, giving in effect an increase in area. The split flaps when deflected about their original axis locations gave slightly higher maximum lift coefficients than conventional trailing-edge flaps, and the lift coefficients were increased still further by moving the axes toward the rear. The highest value of C(sub L max), which was obtained with the largest flap hinged at 90 per cent of the chord from the leading edge, was 2.52 as compared with 1.27 for the basic wing."

Physical Description

7 p. : ill.

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Identifier

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  • : 93R10518
  • URL: http://hdl.handle.net/2060/19930081228 External Link
  • Report No.: NACA-TN-422
  • Center for AeroSpace Information Number: 19930081228
  • Archival Resource Key: ark:/67531/metadc54116

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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

  • May 1932

Added to The UNT Digital Library

  • Nov. 14, 2011, 7:18 p.m.

Description Last Updated

  • May 30, 2017, 1:14 p.m.

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Weick, Fred E. & Harris, Thomas E. The aerodynamic characteristics of a model wing having a split flap deflected downward and moved to the rear, report, May 1932; (digital.library.unt.edu/ark:/67531/metadc54116/: accessed November 25, 2017), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.