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Use of stage-stacking technique for predict- ing over-all performance in multistage axial- flow compressor utilizing interstage-air bleedStage-stacking technique for predicting over-all performance in multistage axial flow turbojet compressor using interstage-air bleed
Document ID
19650003121
Acquisition Source
Legacy CDMS
Document Type
Other - NASA Memorandum (MEMO)
Authors
Lucas, J. G. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 2, 2013
Publication Date
October 1, 1958
Subject Category
Aerodynamics
Report/Patent Number
NASA-MEMO-10-4-58E
Report Number: NASA-MEMO-10-4-58E
Accession Number
65N12722
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
MULTISTAGE COMPRESSOR
TURBOJET ENGINE
AXIAL FLOW COMPRESSOR

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