Theoretical span load distributions and rolling moments for sideslipping wings of arbitrary plan form in incompressible flow

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A method of computing span loads and the resulting rolling moments for sideslipping wings of arbitrary plan form in incompressible flow is derived. The method requires that the span load at zero sideslip be known for the wing under consideration. Because this information is available for a variety of wings, this requirement should not seriously restrict the application of the present method. The basic method derived herein requires a mechanical differentiation and integration to obtain the rolling moment for the general wing in sideslip. For wings having straight leading and trailing edges over each semispan, the rolling moment due to ... continued below

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Queijo, M J January 1, 1956.

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

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  • Main Title: Theoretical span load distributions and rolling moments for sideslipping wings of arbitrary plan form in incompressible flow
  • Series Title: NACA Technical Reports

Description

A method of computing span loads and the resulting rolling moments for sideslipping wings of arbitrary plan form in incompressible flow is derived. The method requires that the span load at zero sideslip be known for the wing under consideration. Because this information is available for a variety of wings, this requirement should not seriously restrict the application of the present method. The basic method derived herein requires a mechanical differentiation and integration to obtain the rolling moment for the general wing in sideslip. For wings having straight leading and trailing edges over each semispan, the rolling moment due to sideslip is given by a simple equation in terms of plan-form parameters and the lateral center of pressure of the lift due to angle of attack. Calculated span loads and rolling-moment parameters are compared with experimental values. The comparison indicates good agreement between calculations and available experimental data.

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  • : 93R21559
  • URL: http://hdl.handle.net/2060/19930092269 External Link
  • Report No.: NACA-TR-1269
  • Center for AeroSpace Information Number: 19930092269
  • Archival Resource Key: ark:/67531/metadc60662

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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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  • January 1, 1956

Added to The UNT Digital Library

  • Nov. 17, 2011, 5:13 p.m.

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  • Feb. 2, 2017, 10:13 p.m.

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Queijo, M J. Theoretical span load distributions and rolling moments for sideslipping wings of arbitrary plan form in incompressible flow, report, January 1, 1956; (digital.library.unt.edu/ark:/67531/metadc60662/: accessed November 23, 2017), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.