Item Details

Static Longitudinal Characteristics at High Subsonic Speeds of a Complete Airplane Model With a Highly Tapered Wing Having the 0.80 Chord Line Unswept and With Several Tail Configurations

by Kenneth W. Goodson
Format
Book; Government Document; Online; EBook
Published
Washington [D.C.] : National Aeronautics and Space Administration, 1961.
Language
English
Series
NASA Technical Note
Summary
An investigation was made at high subsonic speeds of a complete model having a highly tapered wing and several tail configurations. The basic aspect-ratio-4.00 wing had a zero taper and an unswept 0.80 chord line. Several aspect-ratio modifications to the basic wing were made by clipping off portions of the wing tips. The complete model was tested with a chord-plane tail, a T-tail, and a biplane tail (combined T-tail and chord-plane tail). The model was tested in the Langley high-speed 7- by 10-foot tunnel at Mach numbers from 0.60 to 0.92. The data show that, when reduced to the same static margin, all the tail configurations tested on the model provided fairly good stability characteristics, the biplane tail giving the best overall characteristics as regards pitching-moment linearity. Changes in static margin at zero lift coefficient with Mach number were small for the model with these tails over the Mach number range investigated.
Description
57 p. : ill. ; 26 cm.
Mode of access: Internet.
Notes
  • Document ID: 19980232025.
  • "NASA TN D-949."
  • "Supersedes recently declassified NACA Research Memorandum L56J03, by Kenneth W. Goodson."--P. [1].
  • "Langley Research Center, Langley Field, Va."
  • "August 1961."
  • Cover title.
  • Includes bibliographical references (p. 9).
Series Statement
NASA technical note ; D-949
Other Forms
Also available via Internet from NASA Technical Reports Server.
Logo for Copyright Not EvaluatedCopyright Not Evaluated
Technical Details

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    a| Static longitudinal characteristics at high subsonic speeds of a complete airplane model with a highly tapered wing having the 0.80 chord line unswept and with several tail configurations / c| by Kenneth W. Goodson.
    260
      
      
    a| Washington [D.C.] : b| National Aeronautics and Space Administration, c| 1961.
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    a| 57 p. : b| ill. ; c| 26 cm.
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    a| NASA technical note ; v| D-949
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    a| Document ID: 19980232025.
    500
      
      
    a| "NASA TN D-949."
    500
      
      
    a| "Supersedes recently declassified NACA Research Memorandum L56J03, by Kenneth W. Goodson."--P. [1].
    500
      
      
    a| "Langley Research Center, Langley Field, Va."
    500
      
      
    a| "August 1961."
    500
      
      
    a| Cover title.
    504
      
      
    a| Includes bibliographical references (p. 9).
    520
      
      
    a| An investigation was made at high subsonic speeds of a complete model having a highly tapered wing and several tail configurations. The basic aspect-ratio-4.00 wing had a zero taper and an unswept 0.80 chord line. Several aspect-ratio modifications to the basic wing were made by clipping off portions of the wing tips. The complete model was tested with a chord-plane tail, a T-tail, and a biplane tail (combined T-tail and chord-plane tail). The model was tested in the Langley high-speed 7- by 10-foot tunnel at Mach numbers from 0.60 to 0.92. The data show that, when reduced to the same static margin, all the tail configurations tested on the model provided fairly good stability characteristics, the biplane tail giving the best overall characteristics as regards pitching-moment linearity. Changes in static margin at zero lift coefficient with Mach number were small for the model with these tails over the Mach number range investigated.
    530
      
      
    a| Also available via Internet from NASA Technical Reports Server.
    538
      
      
    a| Mode of access: Internet.
    650
      
    7
    a| Subsonic speed. 2| nasat
    650
      
    7
    a| Wing tips. 2| nasat
    650
      
    7
    a| Mach number. 2| nasat
    650
      
    7
    a| Ptiching moments. 2| nasat
    650
      
    7
    a| Aerodynamic coefficients. 2| nasat
    650
      
    7
    a| Aspect ratio. 2| nasat
    650
      
    7
    a| Zero lift. 2| nasat
    650
      
    7
    a| Aircraft models. 2| nasat
    650
      
    7
    a| Static characteristics. 2| nasat
    650
      
    0
    a| Stability of airplanes, Longitudinal.
    710
    1
      
    a| United States. b| National Aeronautics and Space Administration.
    710
    2
      
    a| Langley Research Center.
    974
      
      
    b| UIU c| UIUC d| 20141113 s| google u| uiug.30112106872192 y| 1961 r| pd q| bib

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