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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

Title: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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Note:National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1978
  
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Subject:Compressors -- Aerodynamics
Subject:Turbomachines -- Aerodynamics
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