Item Details

Transonic Single-Mode Flutter and Buffet of a Low Aspect Ratio Wing Having a Subsonic Airfoil Shape

by Larry L. Erickson
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], 1974.
Language
English
Series
NASA Technical Note
Summary
Transonic flutter and buffet results obtained from wind-tunnel tests of a low aspect ratio semispan wing model are presented. The tests were conducted to investigate potential transonic aeroelastic problems of vehicles having subsonic airfoil sections. The model employed NACA 00XX-64 airfoil sections in the streamwise direction and had a 14 deg leading edge sweep angle. Aspect ratio, and average thickness were 4.0, 0.35, and 8 percent, respectively. The model was tested at Mach numbers from 0.6 to 0.95 at angles of attack from 0 deg to 15 deg. Two zero lift flutter conditions were found that involved essentially single normal mode vibrations. With boundary layer trips on the model, flutter occurred in a narrow Mach number range centered at about Mach 0.90. The frequency and motion of this flutter were like that of the first normal mode vibration. With the trips removed flutter occurred at a slightly high Mach number but in a mode strongly resembling that of the second normal mode.
Description
iv, 19 p. : ill. ; 27 cm.
Mode of access: Internet.
Notes
  • Prepared at Ames Research Center.
  • Cover title.
  • Includes bibliographical references (p. 18-19).
Series Statement
NASA technical note ; NASA TN D-7346
Logo for Copyright Not EvaluatedCopyright Not Evaluated
Technical Details

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    a| Erickson, Larry L.
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    a| Transonic single-mode flutter and buffet of a low aspect ratio wing having a subsonic airfoil shape c| by Larry L. Erickson.
    260
      
      
    a| Washington, D.C. : b| National Aeronautics and Space Administration ; a| [Springfield, Va. : b| For sale by the National Technical Information Service], c| 1974.
    300
      
      
    a| iv, 19 p. : b| ill. ; c| 27 cm.
    490
    0
      
    a| NASA technical note ; v| NASA TN D-7346
    500
      
      
    a| Prepared at Ames Research Center.
    500
      
      
    a| Cover title.
    504
      
      
    a| Includes bibliographical references (p. 18-19).
    520
      
      
    a| Transonic flutter and buffet results obtained from wind-tunnel tests of a low aspect ratio semispan wing model are presented. The tests were conducted to investigate potential transonic aeroelastic problems of vehicles having subsonic airfoil sections. The model employed NACA 00XX-64 airfoil sections in the streamwise direction and had a 14 deg leading edge sweep angle. Aspect ratio, and average thickness were 4.0, 0.35, and 8 percent, respectively. The model was tested at Mach numbers from 0.6 to 0.95 at angles of attack from 0 deg to 15 deg. Two zero lift flutter conditions were found that involved essentially single normal mode vibrations. With boundary layer trips on the model, flutter occurred in a narrow Mach number range centered at about Mach 0.90. The frequency and motion of this flutter were like that of the first normal mode vibration. With the trips removed flutter occurred at a slightly high Mach number but in a mode strongly resembling that of the second normal mode.
    538
      
      
    a| Mode of access: Internet.
    650
      
    0
    a| Airplanes x| Wings x| Testing.
    650
      
    0
    a| Buffeting (Aerodynamics)
    650
      
    0
    a| Flutter (Aerodynamics)
    650
      
    0
    a| Aerodynamics, Transonic.
    710
    1
      
    a| United States. b| National Aeronautics and Space Administration.
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    a| Ames Research Center.
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    b| UIU c| UIUC d| 20141113 s| google u| uiug.30112106885327 y| 1974 r| pd q| bib

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