Item Details

Investigation of Engine-Exhaust-Airframe Interference on a Cruise Vehicle at Mach 6

James M. Cubbage and Frank S. Kirkham
Format
Book; Government Document; Online; EBook
Published
Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1971.
Language
English
Variant Title
NASA TN D-6060
Series
NASA Technical Note
SuDoc Number
NAS 1.14:D-6060
Summary
Results from an investigation of the effects of underexpanded engine exhaust flow on the aerodynamic performance and stability of a cruise airplane at Mach 6 are presented. The influence of wing reflex angle and nozzle geometry on exhaust flow interference effects was investigated on a flat-plate model. The experiments were conducted at a free-stream Reynolds number of 17.05 X 10 (to the 6 power) based on the length of the airplane model over a model angle-of-attack range of 0(degrees) to 10(degrees) and at nozzle static-pressure ratios from 1 to approximately 4.
Description
63 p. : ill. ; 27 cm.
Mode of access: Internet.
Notes
Includes bibliographical references (p. 29).
Series Statement
NASA technical note ; D-6060
Logo for No Copyright - United StatesNo Copyright - United States
Technical Details

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    a| Investigation of engine-exhaust-airframe interference on a cruise vehicle at Mach 6 / c| James M. Cubbage and Frank S. Kirkham.
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    a| NASA TN D-6060
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    a| Washington, D.C. : b| National Aeronautics and Space Administration : b| [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], c| 1971.
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    a| 63 p. : b| ill. ; c| 27 cm.
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    a| NASA technical note ; v| D-6060
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    a| Includes bibliographical references (p. 29).
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    a| Results from an investigation of the effects of underexpanded engine exhaust flow on the aerodynamic performance and stability of a cruise airplane at Mach 6 are presented. The influence of wing reflex angle and nozzle geometry on exhaust flow interference effects was investigated on a flat-plate model. The experiments were conducted at a free-stream Reynolds number of 17.05 X 10 (to the 6 power) based on the length of the airplane model over a model angle-of-attack range of 0(degrees) to 10(degrees) and at nozzle static-pressure ratios from 1 to approximately 4.
    538
      
      
    a| Mode of access: Internet.
    650
      
    0
    a| Mach number.
    650
      
    0
    a| Aircraft exhaust emissions.
    650
      
    0
    a| Rockets (Aeronautics) x| Nozzles.
    700
    1
      
    a| Kirkham, F. S.
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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| 20200405 s| google u| uiug.30112106881003 y| 1971 r| pd q| bib t| US fed doc

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