Item Details

Experimental Investigation of the Effects of Compressive Stress on the Flutter of a Curved Panel and a Flat Panel at Supersonic Mach Numbers

by Robert W. Hess and Frederick W. Gibson
Format
Book; Government Document; Online; EBook
Published
Washington, [D.C.] : National Aeronautics and Space Administration, 1962.
Language
English
Series
NASA Technical Note
Summary
"An investigation was made of the effects of compressive stress on the flutter of a curved and a flat panel. The curved panel which was 0.0075-inch-thick stainless steel with a length-width ratio of 2.13 and a radius-to-thickness ratio of 1.133 was tested at a Mach number of 1.97. A flat aluminum panel, 0.032 inch thick with a length-width ratio of 2.13, was tested at Mach numbers of 1.63 to 1.84. The dynamic pressure at flutter decreased with increased axial compressive stress to a point where the panel was loaded to a stress near the calculated critical buckling stress. Beyond this point, the dynamic pressure at flutter increased with increasing compressive stress. The results of the flat-panel flutter tests indicate that caution should be exercised in using empirical panel fluter boundaries."--Summary.
Description
28 p. : ill. ; 26 cm.
Mode of access: Internet.
Notes
  • Document ID: 19620006837.
  • "NASA TN D-1386."
  • "Langley Research Center, Langley Station, Hampton, Va ."
  • "October 1962."
  • Cover title.
  • Includes bibliographical references (p. 11).
Series Statement
NASA technical note ; D-1386
Other Forms
Also available from the NASA Technical Reports Server (http://ntrs.nasa.gov/). Address as of 4/13/07: http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19620006837_1962006837.pdf.
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Technical Details

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    a| Experimental investigation of the effects of compressive stress on the flutter of a curved panel and a flat panel at supersonic Mach numbers / c| by Robert W. Hess and Frederick W. Gibson.
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    a| Washington, [D.C.] : b| National Aeronautics and Space Administration, c| 1962.
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    a| 28 p. : b| ill. ; c| 26 cm.
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    a| NASA technical note ; v| D-1386
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    a| Document ID: 19620006837.
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    a| "NASA TN D-1386."
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    a| "Langley Research Center, Langley Station, Hampton, Va ."
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    a| "October 1962."
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    a| Cover title.
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    a| Includes bibliographical references (p. 11).
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    a| "An investigation was made of the effects of compressive stress on the flutter of a curved and a flat panel. The curved panel which was 0.0075-inch-thick stainless steel with a length-width ratio of 2.13 and a radius-to-thickness ratio of 1.133 was tested at a Mach number of 1.97. A flat aluminum panel, 0.032 inch thick with a length-width ratio of 2.13, was tested at Mach numbers of 1.63 to 1.84. The dynamic pressure at flutter decreased with increased axial compressive stress to a point where the panel was loaded to a stress near the calculated critical buckling stress. Beyond this point, the dynamic pressure at flutter increased with increasing compressive stress. The results of the flat-panel flutter tests indicate that caution should be exercised in using empirical panel fluter boundaries."--Summary.
    530
      
      
    a| Also available from the NASA Technical Reports Server (http://ntrs.nasa.gov/). Address as of 4/13/07: http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19620006837_1962006837.pdf.
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    a| Mode of access: Internet.
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    7
    a| Supersonic speed. 2| nasat
    650
      
    7
    a| Stresses. 2| nasat
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    7
    a| Panel flutter. 2| nasat
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    7
    a| Mach number. 2| nasat
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    7
    a| Flutter. 2| nasat
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    7
    a| Curved panels. 2| nasat
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    7
    a| Compression loads. 2| nasat
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    a| Gibson, Frederick W., c| NASA researcher.
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    a| United States. b| National Aeronautics and Space Administration.
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    a| Langley Research Center.
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    b| UIU c| UIUC d| 20141113 s| google u| uiug.30112106873463 y| 1962 r| pd q| bib

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