Item Details

Effects of Canopy Shape on Low-Speed Aerodynamic Characteristics of a 55⁰ Swept Parawing With Large-Diameter Leading Edges

by Delwin R. Croom, Rodger L. Naeseth, and William C. Sleeman, Jr.
Format
Book; Government Document; Online; EBook
Published
Washington, D.C. : NASA : For sale by the Office of Technical Services, Dept. of Commerce, 1964.
Language
English
Variant Title
Aerodynamic characteristics of a 55⁰ swept parawing with large-diameter leading edges
Series
NASA Technical Note
Abstract
A low-speed wind-tunnel investigation was conducted to study effects of wing-canopy shape on the aerodynamic characteristics and spreader-bar load of a 55⁰ swept parawing having large-diameter leading edges and keel. The canopy-flat-pattern sweep angles investigated on the 55⁰ swept wing were 42.5⁰, 45⁰, 47.5⁰, 50⁰, and 52.5⁰. Several other modifications to the canopy shape were also studied, such as removal of single, double, and compound gores from the rear part of each canopy lobe. A study of the effects of wing-leading-edge sweep angle was made between sweep angles of 50⁰ and 60⁰ and effects of leading-edge diameter were obtained at the basic 55⁰ sweep angle. Effects of keel web height were determined for a constant trailing-edge length and also for trailing-edge lengths that varied with web height.
Description
98, [2] p. : ill. ; 28 cm.
Mode of access: Internet.
Notes
  • "Langley Research Center Langley Station, Hampton, Va."
  • "December 1964"--Cover.
  • "NASA Technical Note NASA TN D-2551"--Cover.
  • This work is part of the library's "Parachute History Collection", donated by the Deutsches Zentrum für Luft- und Raumfahrt e.V. Institut für Flugsystemtechnik, through the American Institute of Aeronautics and Astronautics Aerodynamic Deceleration Systems Technical Committee.
  • Includes bibliographical references.
Series Statement
NASA technical note ; D-2551
Logo for Copyright Not EvaluatedCopyright Not Evaluated
Technical Details

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    a| Effects of canopy shape on low-speed aerodynamic characteristics of a 55⁰ swept parawing with large-diameter leading edges / c| by Delwin R. Croom, Rodger L. Naeseth, and William C. Sleeman, Jr.
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    a| Aerodynamic characteristics of a 55⁰ swept parawing with large-diameter leading edges
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    a| Washington, D.C. : b| NASA : b| For sale by the Office of Technical Services, Dept. of Commerce, c| 1964.
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    a| 98, [2] p. : b| ill. ; c| 28 cm.
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    a| NASA technical note ; v| D-2551
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    a| "Langley Research Center Langley Station, Hampton, Va."
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    a| "December 1964"--Cover.
    500
      
      
    a| "NASA Technical Note NASA TN D-2551"--Cover.
    500
      
      
    a| This work is part of the library's "Parachute History Collection", donated by the Deutsches Zentrum für Luft- und Raumfahrt e.V. Institut für Flugsystemtechnik, through the American Institute of Aeronautics and Astronautics Aerodynamic Deceleration Systems Technical Committee.
    504
      
      
    a| Includes bibliographical references.
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    3
      
    a| A low-speed wind-tunnel investigation was conducted to study effects of wing-canopy shape on the aerodynamic characteristics and spreader-bar load of a 55⁰ swept parawing having large-diameter leading edges and keel. The canopy-flat-pattern sweep angles investigated on the 55⁰ swept wing were 42.5⁰, 45⁰, 47.5⁰, 50⁰, and 52.5⁰. Several other modifications to the canopy shape were also studied, such as removal of single, double, and compound gores from the rear part of each canopy lobe. A study of the effects of wing-leading-edge sweep angle was made between sweep angles of 50⁰ and 60⁰ and effects of leading-edge diameter were obtained at the basic 55⁰ sweep angle. Effects of keel web height were determined for a constant trailing-edge length and also for trailing-edge lengths that varied with web height.
    538
      
      
    a| Mode of access: Internet.
    650
      
    0
    a| Wind tunnels.
    650
      
    0
    a| Drag (Aerodynamics) x| Testing.
    650
      
    0
    a| Airplanes x| Parawings x| Testing.
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    a| Langley Research Center.
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    a| United States. b| National Aeronautics and Space Administration.
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    b| UIU c| UIUC d| 20141113 s| google u| uiug.30112106773721 z| v.2551 y| 1964 r| pd q| bib

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