Item Details

Wind-Tunnel Investigation of Paraglider Models at Supersonic Speeds

by Robert T. Taylor
Format
Book; Government Document; Online; EBook
Published
Washington, D.C. : National Aeronautics and Space Administration, 1961.
Language
English
Series
Technical Note
Abstract
An investigation was made in the Langley Unitary Plan wind tunnel to determine the behavior of paraglider models at moderate to high supersonic speeds. The models were deployed from a sting in the supersonic stream and steady-state aerodynamics performance data were obtained. Maximum values of the lift-drag ratio were about 1.4 at a Mach number of 2.65 and about 1.2 at a Mach number of 4.65. The angles of attack over which the models could be flown were limited by unsteady behavior of the canopy.
Description
16, [3] p. : ill. ; 26 cm.
Mode of access: Internet.
Notes
  • "Technical Note D-985."
  • Caption title.
  • This work is part of the library's "Parachute History Collection" donated by Sandia National Laboratories through the American Institute of Aeronautics and Astronautics Aerodynamic Deceleration Systems Technical Committee.
  • Includes bibliographical references (p. 5).
Series Statement
Technical note ; D-985
Logo for No Copyright - United StatesNo Copyright - United States
Technical Details

  • LEADER 02274cam a2200445Ia 4500
    001 011448580
    003 MiAaHDL
    005 20141009010000.0
    006 m d
    007 cr bn ---auaua
    008 061020s1961 dcua b f000 0 eng d
    035
      
      
    a| sdr-uiuc6395630
    035
      
      
    a| (OCoLC)73789830
    040
      
      
    a| LHL c| LHL d| OCLCQ
    049
      
      
    a| UIUU
    090
      
      
    a| TL574.A4 b| T39 1961
    100
    1
      
    a| Taylor, Robert T.
    245
    1
    0
    a| Wind-tunnel investigation of paraglider models at supersonic speeds / c| by Robert T. Taylor.
    260
      
      
    a| Washington, D.C. : b| National Aeronautics and Space Administration, c| 1961.
    300
      
      
    a| 16, [3] p. : b| ill. ; c| 26 cm.
    490
    0
      
    a| Technical note ; v| D-985
    500
      
      
    a| "Technical Note D-985."
    500
      
      
    a| Caption title.
    500
      
      
    a| This work is part of the library's "Parachute History Collection" donated by Sandia National Laboratories through the American Institute of Aeronautics and Astronautics Aerodynamic Deceleration Systems Technical Committee.
    504
      
      
    a| Includes bibliographical references (p. 5).
    520
    3
      
    a| An investigation was made in the Langley Unitary Plan wind tunnel to determine the behavior of paraglider models at moderate to high supersonic speeds. The models were deployed from a sting in the supersonic stream and steady-state aerodynamics performance data were obtained. Maximum values of the lift-drag ratio were about 1.4 at a Mach number of 2.65 and about 1.2 at a Mach number of 4.65. The angles of attack over which the models could be flown were limited by unsteady behavior of the canopy.
    538
      
      
    a| Mode of access: Internet.
    650
      
    0
    a| Wind tunnels.
    650
      
    0
    a| Aerodynamics, Supersonic.
    650
      
    0
    a| Gliders (Aeronautics) x| Models x| Testing.
    650
      
    0
    a| Airplanes x| Models x| Parawings x| Testing.
    710
    1
      
    a| United States. b| National Aeronautics and Space Administration.
    974
      
      
    b| UIU c| UIUC d| 20141113 s| google u| uiug.30112106914879 y| 1961 r| pd q| bib

Access online

Google Preview