An investigation of the low-speed stability and control characteristics of swept-forward and swept-back wing in the Ames 40- by 80-foot wind tunnel

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Description

An investigation has been made at large scale of the characteristics of highly swept wings. Data were obtained at several angles of sideslip on wings having angles of sweep of plus or minus 45 degrees, plus or minus 30 degrees, and 0 degrees. The airfoil sections of the wings varied from approximately NACA 0015 at the root to NACA 23009 at the tip. Each wing was investigated with flaps under flection, partial-span split flaps deflected 60 degrees, full-span split flaps defected 60 degrees and split-flap-type ailerons deflected plus or minus 15 degrees. Values of maximum lift were obtained at Reynolds ... continued below

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Mccormack, Gerald M & Stevens, Victor I , Jr June 10, 1947.

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  • Main Title: An investigation of the low-speed stability and control characteristics of swept-forward and swept-back wing in the Ames 40- by 80-foot wind tunnel
  • Series Title: NACA Research Memorandums

Description

An investigation has been made at large scale of the characteristics of highly swept wings. Data were obtained at several angles of sideslip on wings having angles of sweep of plus or minus 45 degrees, plus or minus 30 degrees, and 0 degrees. The airfoil sections of the wings varied from approximately NACA 0015 at the root to NACA 23009 at the tip. Each wing was investigated with flaps under flection, partial-span split flaps deflected 60 degrees, full-span split flaps defected 60 degrees and split-flap-type ailerons deflected plus or minus 15 degrees. Values of maximum lift were obtained at Reynolds numbers raging from 5.7 to 9.2 times 10 to the 6th power. In this report the summarized results are compared with the predictions made by use of the simplified theory for the effect of sweep and with existing small-scale data. The basic wind-tunnel results from which these summary data were taken are included in an appendix. The primary problems accompanying the use of weep as revealed by this investigation are the loss in maximum lift, the high effective dihedral, and the sharp reduction in lateral-control effectiveness. In general, simple theory enables good predictions to be made of the gross effects of sweep but further refinements are necessary to obtain the accuracy required for design purposes. In cases where comparisons can be made, the indications are that, as sweep increases, scale effects diminish and large-scale results approach small-scale results.

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  • : 93R14967
  • URL: http://hdl.handle.net/2060/19930085677 External Link
  • Report No.: NACA-RM-A6K15
  • Center for AeroSpace Information Number: 19930085677
  • Archival Resource Key: ark:/67531/metadc58054

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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

  • June 10, 1947

Added to The UNT Digital Library

  • Nov. 16, 2011, 7:33 a.m.

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  • Jan. 30, 2017, 4 p.m.

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Mccormack, Gerald M & Stevens, Victor I , Jr. An investigation of the low-speed stability and control characteristics of swept-forward and swept-back wing in the Ames 40- by 80-foot wind tunnel, report, June 10, 1947; (digital.library.unt.edu/ark:/67531/metadc58054/: accessed November 20, 2017), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.