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Exhaust Nozzle Plume Effects on Sonic Boom Test Results for Isolated Nozzles [electronic resource]

Raymond S. Castner ; prepared for the 28th Applied Aerodynamics Conference sponsored by the American Institute of Aeronautics and Astronautics, Chicago, Illinois, June 28-July 1, 20
Format
EBook; Book; Government Document; Online
Published
Cleveland, Ohio : National Aeronautics and Space Administration, Glenn Research Center, [2011]
Language
English
Series
NASA/TM
NASA Technical Memorandum
SuDoc Number
NAS 1.15:2011-217137
Description
1 online resource (16 p.) : col. ill.
Notes
  • Title from title screen (viewed on Aug. 30, 2012).
  • "December 2011."
  • "AIAA-2010-4936."
  • Includes bibliographical references (p. 16).
Series Statement
NASA/TM ; 2011-217137
NASA technical memorandum 217137
Copyright Not EvaluatedCopyright Not Evaluated
Technical Details
  • Access in Virgo Classic
  • Staff View

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    a| Exhaust nozzle plume effects on sonic boom test results for isolated nozzles h| [electronic resource] / c| Raymond S. Castner ; prepared for the 28th Applied Aerodynamics Conference sponsored by the American Institute of Aeronautics and Astronautics, Chicago, Illinois, June 28-July 1, 20.
    260
      
      
    a| Cleveland, Ohio : b| National Aeronautics and Space Administration, Glenn Research Center, c| [2011]
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    a| Title from title screen (viewed on Aug. 30, 2012).
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    a| Includes bibliographical references (p. 16).
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    a| "AIAA-2010-4936."
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    a| Exhaust nozzles. 2| nasat
    650
      
    7
    a| Nozzle flow. 2| nasat
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    7
    a| Plumes. 2| nasat
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    7
    a| Supersonic aircraft. 2| nasat
    650
      
    7
    a| Computational fluid dynamics. 2| nasat
    650
      
    7
    a| Nozzle geometry. 2| nasat
    650
      
    7
    a| Pressure ratio. 2| nasat
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    a| Shock waves. 2| nasat
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    7
    a| Elastic waves. 2| nasat
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