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
1978 by National Aeronautics and Space Administration, Scientific and Technical Information Office in Washington, D.C, [Springfield, Va.] .
Written in English
|Statement||Royce D. Moore and Lonnie Reid.|
|Series||NASA technical paper -- 1338, 1659.|
|Contributions||Reid, Lonnie., Lewis Research Center., United States. National Aeronautics and Space Administration. Scientific and Technical Information Office.|
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