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Saturday, April 25, 2020 | History

2 edition of Performance of single-stage axial-flow transonic compressor with rotor and stator aspect ratios of 1.19 and 1.26, respectively, and with design pressure ratio of 2.05 found in the catalog.

Performance of single-stage axial-flow transonic compressor with rotor and stator aspect ratios of 1.19 and 1.26, respectively, and with design pressure ratio of 2.05

Royce D. Moore

Performance of single-stage axial-flow transonic compressor with rotor and stator aspect ratios of 1.19 and 1.26, respectively, and with design pressure ratio of 2.05

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Published by National Aeronautics and Space Administration, Scientific and Technical Information Office in Washington, D.C, [Springfield, Va.] .
Written in English

    Subjects:
  • Turbomachines -- Aerodynamics.,
  • Compressors -- Aerodynamics.

  • Edition Notes

    StatementRoyce D. Moore and Lonnie Reid.
    SeriesNASA technical paper -- 1338, 1659.
    ContributionsReid, Lonnie., Lewis Research Center., United States. National Aeronautics and Space Administration. Scientific and Technical Information Office.
    The Physical Object
    Paginationv. :
    ID Numbers
    Open LibraryOL17542431M


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Performance of single-stage axial-flow transonic compressor with rotor and stator aspect ratios of 1.19 and 1.26, respectively, and with design pressure ratio of 2.05 by Royce D. Moore Download PDF EPUB FB2