Item Details

Comparison of Experimental and Theoretical Static Aeroelastic Loads and Deflections of a Thin 45° Wing in Supersonic Flow

by Floyd V. Bennett
Format
Book; Government Document; Online; EBook
Published
Washington, [D.C.] : National Aeronautical and Space Administration, 1961.
Language
English
Series
NASA Technical Note
Summary
Wind tunnel tests showing the effects of static aeroelasticity for a thin 45° delta wing in supersonic flow are presented and compared with theory in the Mach number range 1.30 t o 4.00. Calculated deformations, normal-force coefficients, and pitching-moment coefficients based on a linearized potential theory for subsonic leading edges at a Mach number of 1.30 and a linearized potential theory for supersonic leading edges at Mach numbers of 1.64, 3.00, and 4.00 are shown to compare favorably with the wind-tunnel results.
Description
41 p. : ill. ; 26 cm.
Mode of access: Internet.
Notes
  • Document ID: 20040008163.
  • "NASA TN D-974."
  • "Langley Research Center, Langley Air Force, Va."
  • "October 1961."
  • Cover title.
  • Includes bibliographical references (p. 25).
Series Statement
NASA technical note ; D-974
Logo for No Copyright - United StatesNo Copyright - United States
Technical Details

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    a| Comparison of experimental and theoretical static aeroelastic loads and deflections of a thin 45° wing in supersonic flow / c| by Floyd V. Bennett.
    260
      
      
    a| Washington, [D.C.] : b| National Aeronautical and Space Administration, c| 1961.
    300
      
      
    a| 41 p. : b| ill. ; c| 26 cm.
    490
      
    0
    a| NASA technical note ; v| D-974
    500
      
      
    a| Document ID: 20040008163.
    500
      
      
    a| "NASA TN D-974."
    500
      
      
    a| "Langley Research Center, Langley Air Force, Va."
    500
      
      
    a| "October 1961."
    500
      
      
    a| Cover title.
    504
      
      
    a| Includes bibliographical references (p. 25).
    520
      
      
    a| Wind tunnel tests showing the effects of static aeroelasticity for a thin 45° delta wing in supersonic flow are presented and compared with theory in the Mach number range 1.30 t o 4.00. Calculated deformations, normal-force coefficients, and pitching-moment coefficients based on a linearized potential theory for subsonic leading edges at a Mach number of 1.30 and a linearized potential theory for supersonic leading edges at Mach numbers of 1.64, 3.00, and 4.00 are shown to compare favorably with the wind-tunnel results.
    538
      
      
    a| Mode of access: Internet.
    650
      
    0
    a| Delta wing airplanes.
    650
      
    0
    a| Aerodynamics, Supersonic.
    650
      
    0
    a| Aerodynamic load.
    650
      
    0
    a| Aeroelasticity.
    710
    1
      
    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.30112106914945 y| 1961 r| pd q| bib

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