Item Details

Panel Flutter Tests on Full-Scale X-15 Lower Vertical Stabilizer at Mach Number of 3.0

by Herman L. Bohon
Format
Book; Government Document; Online; EBook
Published
Washington, [D.C.] : National Aeronautics and Space Administration, 1962.
Language
English
Series
NASA Technical Note
Summary
"Panel flutter tests were conducted on two-full scale vertical stabilizers of the X-15 airplane at a Mach number of 3.0 in the Langley 9- by 6-foot thermal structures tunnel at dynamic pressures from 1,500 psf to 5,000 psf and stagnation temperatures from 300° F to 600° F. Flutter boundaries were obtained for four of the five distinct types of panels which make up the vertical sides of the stabilizers. The boundaries consisted of a flat-panel boundary and a thermally buckled-panel boundary. The flat-panel boundaries were characterized by a reduction in dynamic pressure with increasing skin temperature; whereas, after thermal buckling the trend was reversed. The minimum dynamic pressure for flutter occurred at the intersection of the flat-panel and buckled-panel boundaries and represented a large reduction in the dynamic pressure over the extrapolated, unstressed value. As a result of panel flutter, three of the five distinct types of panels were modified to provide the required flutter margin on the design flight dynamic pressure of the aircraft."--Summary.
Description
61 p. : ill. ; 26 cm.
Mode of access: Internet.
Notes
  • Document ID: 19620006698.
  • "NASA TN D-1385."
  • "Langley Research Center, Langley Station, Hampton, Va."
  • "October 1962."
  • Cover title.
  • Includes bibliographical references (p. 17).
Series Statement
NASA technical note ; D-1385
Other Forms
Also available from the NASA Technical Reports Server (http://ntrs.nasa.gov/). Address as of 4/12/07: http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19620006698_1962006698.pdf.
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Technical Details

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    a| Panel flutter tests on full-scale X-15 lower vertical stabilizer at Mach number of 3.0 / c| by Herman L. Bohon.
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    a| Washington, [D.C.] : b| National Aeronautics and Space Administration, c| 1962.
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    a| 61 p. : b| ill. ; c| 26 cm.
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    a| Document ID: 19620006698.
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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. 17).
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    a| "Panel flutter tests were conducted on two-full scale vertical stabilizers of the X-15 airplane at a Mach number of 3.0 in the Langley 9- by 6-foot thermal structures tunnel at dynamic pressures from 1,500 psf to 5,000 psf and stagnation temperatures from 300° F to 600° F. Flutter boundaries were obtained for four of the five distinct types of panels which make up the vertical sides of the stabilizers. The boundaries consisted of a flat-panel boundary and a thermally buckled-panel boundary. The flat-panel boundaries were characterized by a reduction in dynamic pressure with increasing skin temperature; whereas, after thermal buckling the trend was reversed. The minimum dynamic pressure for flutter occurred at the intersection of the flat-panel and buckled-panel boundaries and represented a large reduction in the dynamic pressure over the extrapolated, unstressed value. As a result of panel flutter, three of the five distinct types of panels were modified to provide the required flutter margin on the design flight dynamic pressure of the aircraft."--Summary.
    530
      
      
    a| Also available from the NASA Technical Reports Server (http://ntrs.nasa.gov/). Address as of 4/12/07: http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19620006698_1962006698.pdf.
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    a| Mode of access: Internet.
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    a| Panel flutter. 2| nasat
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    a| Mach number. 2| nasat
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    a| Aerodynamic heating. 2| nasat
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