The effect of partial-span split flaps on the aerodynamic characteristics of a Clark Y wing

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Description

Aerodynamic force tests were made in the N.A.C.A. 7 by 10 foot wind tunnel on a model Clark Y wing with a 20 percent chord split flap deflected 60 degrees downward. The tests were made to determine the effect of partial-span split flaps, located at various positions along the wing span on the aerodynamic characteristics of the wing-and-flap combination. The different lengths and locations of the flaps were obtained by cutting off portions of a full-span flap, first from the tips and then from the center. The results are given in the form of curves of lift, drag, and center ... continued below

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Wenzinger, Carl J. September 1, 1933.

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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 106 times , with 13 in the last month . More information about this report can be viewed below.

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  • Main Title: The effect of partial-span split flaps on the aerodynamic characteristics of a Clark Y wing
  • Series Title: NACA Technical Notes

Description

Aerodynamic force tests were made in the N.A.C.A. 7 by 10 foot wind tunnel on a model Clark Y wing with a 20 percent chord split flap deflected 60 degrees downward. The tests were made to determine the effect of partial-span split flaps, located at various positions along the wing span on the aerodynamic characteristics of the wing-and-flap combination. The different lengths and locations of the flaps were obtained by cutting off portions of a full-span flap, first from the tips and then from the center. The results are given in the form of curves of lift, drag, and center of pressure. They show that with partial-span split flaps both the lift and drag are less than with full-span flaps; that the lift for a given length of flap is somewhat greater when the partial span is located at the center of the wing than when it is located at the tip portion, and that the drag for a given length of flap is the same regardless of the location over the flap with respect to the wing span.

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  • : 93R10564
  • URL: http://hdl.handle.net/2060/19930081274 External Link
  • Report No.: NACA-TN-472
  • Center for AeroSpace Information Number: 19930081274
  • Archival Resource Key: ark:/67531/metadc54161

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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

  • September 1, 1933

Added to The UNT Digital Library

  • Nov. 14, 2011, 7:18 p.m.

Description Last Updated

  • Feb. 6, 2017, 6:53 p.m.

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Wenzinger, Carl J. The effect of partial-span split flaps on the aerodynamic characteristics of a Clark Y wing, report, September 1, 1933; (digital.library.unt.edu/ark:/67531/metadc54161/: accessed December 18, 2017), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.