Item Details

Experimental Investigation of Orthotropic Panel Flutter at Arbitrary Yaw Angles, and Comparison With Theory

by Peter Shyprykevich
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 [distributor], 1973.
Language
English
Series
NASA Contractor Report
Summary
Flutter characteristics for yaw angles between 15 deg and 90 deg were determined experimentally for two types of corrugation-stiffened panels: those with weak twisting stiffness and those with strong twisting stiffness. By mounting the panels on a remotely controlled turntable, good definition of the flutter boundaries was obtained by rotating the panels into and out of flutter. Flutter tests were conducted at M = 2 and M = 1.6. Before testing, vibration tests and analyses were also performed. The experimental flutter data is compared with flutter theory for orthotropic panels utilizing quasi-steady aerodynamics. Five different corrugated panels were tested consisting of one single skin panel having a length-to-width ratio of 5 on clamped supports and four different square double skin panels on discrete flexible supports. The investigation indicated that flutter speed for corrugated panels is highly dependent on yaw angle. Reasonable flutter correlation between analysis and test was obtained for moderate yaw angles, but extreme sensitivity to structural parameters made the correlation at large yaw angles uncertain.
Description
33 p. : ill. ; 27 cm.
Mode of access: Internet.
Notes
  • "NASA CR-2265."
  • "May 1973."
  • Cover title.
  • Includes bibliographical references (p. 14).
Series Statement
NASA contractor report ; NASA CR-2265
Logo for No Copyright - United StatesNo Copyright - United States
Technical Details

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    a| TL521.3.C6 b| A3 no. 2265
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    a| Shyprykevich, Peter.
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    a| Experimental investigation of orthotropic panel flutter at arbitrary yaw angles, and comparison with theory / c| by Peter Shyprykevich.
    260
      
      
    a| Washington, D.C. : b| National Aeronautics and Space Administration ; a| Springfield, Va. : b| For sale by the National Technical Information Service [distributor], c| 1973.
    300
      
      
    a| 33 p. : b| ill. ; c| 27 cm.
    490
      
    0
    a| NASA contractor report ; v| NASA CR-2265
    500
      
      
    a| "NASA CR-2265."
    500
      
      
    a| "May 1973."
    500
      
      
    a| Cover title.
    504
      
      
    a| Includes bibliographical references (p. 14).
    520
      
      
    a| Flutter characteristics for yaw angles between 15 deg and 90 deg were determined experimentally for two types of corrugation-stiffened panels: those with weak twisting stiffness and those with strong twisting stiffness. By mounting the panels on a remotely controlled turntable, good definition of the flutter boundaries was obtained by rotating the panels into and out of flutter. Flutter tests were conducted at M = 2 and M = 1.6. Before testing, vibration tests and analyses were also performed. The experimental flutter data is compared with flutter theory for orthotropic panels utilizing quasi-steady aerodynamics. Five different corrugated panels were tested consisting of one single skin panel having a length-to-width ratio of 5 on clamped supports and four different square double skin panels on discrete flexible supports. The investigation indicated that flutter speed for corrugated panels is highly dependent on yaw angle. Reasonable flutter correlation between analysis and test was obtained for moderate yaw angles, but extreme sensitivity to structural parameters made the correlation at large yaw angles uncertain.
    536
      
      
    a| Prepared by Grumman Aerospace Corporation, Bethpage, NY for Langley Research Center b| NAS1-10635-6
    538
      
      
    a| Mode of access: Internet.
    650
      
    0
    a| Hypersonic planes x| Materials x| Testing.
    650
      
    0
    a| Yawing (Aerodynamics)
    650
      
    0
    a| Flutter (Aerodynamics)
    650
      
    7
    a| Wind tunnel tests. 2| nasat
    650
      
    7
    a| Structural strain. 2| nasat
    650
      
    7
    a| Aerodynamic characteristics. 2| nasat
    650
      
    7
    a| Yaw. 2| nasat
    650
      
    7
    a| Panel flutter. 2| nasat
    650
      
    7
    a| Orthotropism. 2| nasat
    650
      
    7
    a| Corrugated plates. 2| nasat
    710
    2
      
    a| Langley Research Center.
    710
    2
      
    a| Grumman Aerospace Corporation.
    974
      
      
    b| UIU c| UIUC d| 20141113 s| google u| uiug.30112106861310 y| 1973 r| pd q| bib

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