Method for calculating lift distributions for unswept wings with flaps or ailerons by use of nonlinear section lift data

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Description

A method is presented which allows the use of nonlinear section lift data in the calculation of the spanwise lift distribution of unswept wings with flaps or ailerons. This method is based upon lifting line theory and is an extension to the method described in NACA rep. 865. The mathematical treatment of the discontinuity in absolute angle of attack at the end of the flap or aileron involves the use of a correction factor which accounts for the inability of a limited trigonometric series to represent adequately the spanwise lift distribution. A treatment of the apparent discontinuity in maximum section … continued below

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63 p. : ill.

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Sivells, James C. & Westrick, Gertrude C. November 13, 1950.

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

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  • Main Title: Method for calculating lift distributions for unswept wings with flaps or ailerons by use of nonlinear section lift data
  • Series Title: NACA Technical Reports

Description

A method is presented which allows the use of nonlinear section lift data in the calculation of the spanwise lift distribution of unswept wings with flaps or ailerons. This method is based upon lifting line theory and is an extension to the method described in NACA rep. 865. The mathematical treatment of the discontinuity in absolute angle of attack at the end of the flap or aileron involves the use of a correction factor which accounts for the inability of a limited trigonometric series to represent adequately the spanwise lift distribution. A treatment of the apparent discontinuity in maximum section lift coefficient is also described. Simplified computing forms containing detailed examples are given for both symmetrical and asymmetrical lift distributions. A few comparisons of calculated characteristics with those obtained experimentally are also presented.

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63 p. : ill.

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  • Accession or Local Control No: 93R21422
  • URL: http://hdl.handle.net/2060/19930092132 External Link
  • Report No.: NACA-TR-1090
  • Center for AeroSpace Information Number: 19930092132
  • Archival Resource Key: ark:/67531/metadc60450

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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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  • November 13, 1950

Added to The UNT Digital Library

  • Nov. 17, 2011, 5:13 p.m.

Description Last Updated

  • April 12, 2018, 12:40 p.m.

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Sivells, James C. & Westrick, Gertrude C. Method for calculating lift distributions for unswept wings with flaps or ailerons by use of nonlinear section lift data, report, November 13, 1950; (https://digital.library.unt.edu/ark:/67531/metadc60450/: accessed September 16, 2026), University of North Texas Libraries, UNT Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.

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