Item Details

Transonic Aerodynamic Loading Characteristics of a Wing-Body-Tail Combination Having 52.5° Sweptback Wing of Aspect Ratio 3 With Conical Wing Camber and Body Indentation for a Design Mach Number [Square Root of] 2

by Marlowe D. Cassetti, Richard J. Re, and William B. Igoe
Format
Book; Government Document; Online; EBook
Published
Washington, [D.C.] : National Aeronautics and Space Administration, 1961.
Language
English
Series
NASA Technical Note
Summary
An investigation has been made of the effects of conical wing camber and body indentation according to the supersonic area rule on the aerodynamic wing loading characteristics of a wing-body-tail configuration at transonic speeds. The wing aspect ratio was 3, taper ratio was 0.1, and quarter-chord-line sweepback was 52.5° with 3-percent-thick airfoil sections. The tests were conducted in the Langley 16-foot transonic tunnel at Mach numbers from 0.80 to 1.05 and at angles of attack from 0° to 14°, with Reynolds numbers based on mean aerodynamic chord varying from 7 x 10⁶ to 8 x 10⁶. Conical camber delayed wing-tip stall and reduced the severity of the accompanying longitudinal instability but did not appreciably affect the spanwise load distribution at angles of attack below tip stall. Body indentation reduced to transonic chordwise center-of-pressure travel from about 8 percent to 5 percent of the mean aerodynamic chord.
Description
99 p. : ill. ; 26 cm.
Mode of access: Internet.
Notes
  • Document ID: 19980227081.
  • "NASA TN D-971."
  • "Langley Research Center, Langley Air Force Base, Va."
  • "October 1961."
  • Cover title.
  • Includes bibliographical references (p. 9).
Series Statement
NASA technical note ; D-971
Other Forms
Also available via Internet from NASA Technical Reports Server.
Logo for Copyright Not EvaluatedCopyright Not Evaluated
Technical Details

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    a| Transonic aerodynamic loading characteristics of a wing-body-tail combination having 52.5° sweptback wing of aspect ratio 3 with conical wing camber and body indentation for a design Mach number [square root of] 2 / c| by Marlowe D. Cassetti, Richard J. Re, and William B. Igoe.
    260
      
      
    a| Washington, [D.C.] : b| National Aeronautics and Space Administration, c| 1961.
    300
      
      
    a| 99 p. : b| ill. ; c| 26 cm.
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    0
    a| NASA technical note ; v| D-971
    500
      
      
    a| Document ID: 19980227081.
    500
      
      
    a| "NASA TN D-971."
    500
      
      
    a| "Langley Research Center, Langley Air Force Base, Va."
    500
      
      
    a| "October 1961."
    500
      
      
    a| Cover title.
    504
      
      
    a| Includes bibliographical references (p. 9).
    520
      
      
    a| An investigation has been made of the effects of conical wing camber and body indentation according to the supersonic area rule on the aerodynamic wing loading characteristics of a wing-body-tail configuration at transonic speeds. The wing aspect ratio was 3, taper ratio was 0.1, and quarter-chord-line sweepback was 52.5° with 3-percent-thick airfoil sections. The tests were conducted in the Langley 16-foot transonic tunnel at Mach numbers from 0.80 to 1.05 and at angles of attack from 0° to 14°, with Reynolds numbers based on mean aerodynamic chord varying from 7 x 10⁶ to 8 x 10⁶. Conical camber delayed wing-tip stall and reduced the severity of the accompanying longitudinal instability but did not appreciably affect the spanwise load distribution at angles of attack below tip stall. Body indentation reduced to transonic chordwise center-of-pressure travel from about 8 percent to 5 percent of the mean aerodynamic chord.
    530
      
      
    a| Also available via Internet from NASA Technical Reports Server.
    538
      
      
    a| Mode of access: Internet.
    650
      
    7
    a| Angle of attack. 2| nasat
    650
      
    7
    a| Aspect ratio. 2| nasat
    650
      
    7
    a| Transonic wind tunnels. 2| nasat
    650
      
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    a| Aerodynamic characteristics. 2| nasat
    650
      
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    a| Airfoil profiles. 2| nasat
    650
      
    7
    a| Supersonic speed. 2| nasat
    650
      
    7
    a| Sweptback wings. 2| nasat
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    7
    a| Wing loading. 2| nasat
    650
      
    7
    a| Wind tunnel tests. 2| nasat
    650
      
    7
    a| Aerodynamic loads. 2| nasat
    700
    1
      
    a| Igoe, William B.
    700
    1
      
    a| Re, Richard J.
    710
    1
      
    a| United States. b| National Aeronautics and Space Administration.
    710
    2
      
    a| Langley Research Center.
    974
      
      
    b| UIU c| UIUC d| 20141113 s| google u| uiug.30112106914986 y| 1961 r| pd q| bib

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