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Performance of low-pressure-ratio fan stage at two off-design blade setting anglesThe overall and blade-element performance of a low pressure ratio, low tip speed fan stage at design speed is presented for tow off-design rotor blade angle settings. The rotor design tip speed is 243.8 m/sec and weight flow per unit annulus area is 175.8 kg/sec. Design weight flow and pressure ratio are 29.9 kg/sec and 1.151, respectively.
Document ID
19770013087
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Kovich, G. (NASA Lewis Research Center Cleveland, OH, United States)
Tysl, E. R. (NASA Lewis Research Center Cleveland, OH, United States)
Moore, R. D. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 3, 2013
Publication Date
March 1, 1977
Subject Category
Aerodynamics
Report/Patent Number
E-8578
NASA-TM-X-3447
Report Number: E-8578
Report Number: NASA-TM-X-3447
Accession Number
77N20031
Funding Number(s)
PROJECT: RTOP 505-04
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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