Damping in pitch and roll of triangular wings at supersonic speeds

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Description

A method is derived for calculating the damping coefficients in pitch and roll for a series of triangular wings and a restricted series of sweptback wings at supersonic speeds. The elementary "supersonic source" solution of the linearized equation of motion is used to find the potential function of a line of doublets, and the flows are obtained by surface distributions of these doublet lines. The damping derivatives for triangular wings are found to be a function of the ratio of the tangent of the apex angle to the tangent of the Mach angle. As this ratio becomes equal to and ... continued below

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59 - 67 p. : ill.

Creation Information

Brown, Clinton E. & Adams, Mac C. December 12, 1947.

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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: Damping in pitch and roll of triangular wings at supersonic speeds
  • Series Title: NACA Technical Reports

Description

A method is derived for calculating the damping coefficients in pitch and roll for a series of triangular wings and a restricted series of sweptback wings at supersonic speeds. The elementary "supersonic source" solution of the linearized equation of motion is used to find the potential function of a line of doublets, and the flows are obtained by surface distributions of these doublet lines. The damping derivatives for triangular wings are found to be a function of the ratio of the tangent of the apex angle to the tangent of the Mach angle. As this ratio becomes equal to and greater than 1.0 for triangular wings, the damping derivatives, in pitch and in roll, become constant. The damping derivative in roll becomes equal to one-half the value calculated for an infinite rectangular wing, and the damping derivative in pitch for pitching about the apex becomes equal to 3.375 times that of an infinite rectangular wing.

Physical Description

59 - 67 p. : ill.

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  • Accession or Local Control No: 93R21251
  • URL: http://hdl.handle.net/2060/19930091961 External Link
  • Report No.: NACA-TR-892
  • Center for AeroSpace Information Number: 19930091961
  • Archival Resource Key: ark:/67531/metadc60198

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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

  • December 12, 1947

Added to The UNT Digital Library

  • Nov. 17, 2011, 5:13 p.m.

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  • April 9, 2018, 3 p.m.

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Brown, Clinton E. & Adams, Mac C. Damping in pitch and roll of triangular wings at supersonic speeds, report, December 12, 1947; (digital.library.unt.edu/ark:/67531/metadc60198/: accessed July 17, 2018), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.