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Subsonic Aerodynamic Characteristics of a Large-Scale 1.075-Pressure-Ratio Tip-Turbine Cruise-Fan Propulsion System at Angle of AttackWind tunnel tests of subsonic aerodynamic characteristics of large scale tip turbine cruise fan with 1.075 pressure ratio at angle of attack
Document ID
19690025197
Acquisition Source
Headquarters
Document Type
Other - NASA Technical Note (TN)
Authors
Capone, Francis J. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 2, 2013
Publication Date
August 1, 1969
Subject Category
Propulsion Systems
Report/Patent Number
NASA-TN-D-5316
Report Number: NASA-TN-D-5316
Accession Number
69N34575
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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