Item Details

Lifting-Surface Theory for Calculating the Loading Induced on a Wing by a Flap

by Wayne Johnson
Format
Book; Government Document; Online; EBook
Published
Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1972.
Language
English
Series
NASA Technical Note
Summary
A method is described for using lifting-surface theory to obtain the pressure distribution on a wing with a trailing-edge flap or control surface. The loading has a logarithmic singularity at the flap edges, which may be determined directly by the method of matched asymptotic expansions. Expressions are given for the singular flap loading for various flap hinge line and side edge geometries, both for steady and unsteady flap deflection. The regular part of the flap loading must be obtained by inverting the lifting-surface-theory integral equation relating the pressure and the downwash on the wing: procedures are described to accomplish this for a general wing and flap geometry. The method is applied to several example wings, and the results are compared with experimental data. Theory and test correlate well.
Description
v, 15 p. : ill. ; 27 cm.
Mode of access: Internet.
Notes
  • Prepared at Ames Research Center and the U.S. Army Air Mobility R&D Laboratory.
  • Cover title.
  • Bibliography: p. 15.
Series Statement
NASA technical note ; NASA TN D-6798
Logo for No Copyright - United StatesNo Copyright - United States
Technical Details

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    a| Johnson, Wayne, d| 1946-
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    a| Lifting-surface theory for calculating the loading induced on a wing by a flap c| by Wayne Johnson.
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    a| Washington, D.C. : b| National Aeronautics and Space Administration ; a| [Springfield, Va. : b| For sale by the National Technical Information Service], c| 1972.
    300
      
      
    a| v, 15 p. : b| ill. ; c| 27 cm.
    490
    0
      
    a| NASA technical note ; v| NASA TN D-6798
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    a| Prepared at Ames Research Center and the U.S. Army Air Mobility R&D Laboratory.
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    a| Cover title.
    504
      
      
    a| Bibliography: p. 15.
    520
      
      
    a| A method is described for using lifting-surface theory to obtain the pressure distribution on a wing with a trailing-edge flap or control surface. The loading has a logarithmic singularity at the flap edges, which may be determined directly by the method of matched asymptotic expansions. Expressions are given for the singular flap loading for various flap hinge line and side edge geometries, both for steady and unsteady flap deflection. The regular part of the flap loading must be obtained by inverting the lifting-surface-theory integral equation relating the pressure and the downwash on the wing: procedures are described to accomplish this for a general wing and flap geometry. The method is applied to several example wings, and the results are compared with experimental data. Theory and test correlate well.
    538
      
      
    a| Mode of access: Internet.
    650
      
    0
    a| Airplanes x| Wings.
    650
      
    0
    a| Aerodynamic load x| Measurement.
    650
      
    0
    a| Flaps (Airplanes)
    650
      
    0
    a| Lift (Aerodynamics) x| Mathematical models.
    710
    1
      
    a| United States. b| National Aeronautics and Space Administration.
    710
    2
      
    a| Ames Research Center.
    710
    2
      
    a| U.S. Army Air Mobility Research and Development Laboratory.
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    b| UIU c| UIUC d| 20141113 s| google u| uiug.30112106883884 y| 1972 r| pd q| bib

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