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Effect on fan flow characteristics of length and axial location of a cascade thrust reverserA series of static tests were conducted on a model fan with a diameter of 14.0 cm to determine the fan operating characteristics, the inlet static pressure contours, the fan-exit total and static pressure contours, and the fan-exit pressure distortion parameters associated with the installation of a partial-circumferential-emission cascade thrust reverser. The tests variables included the cascade axial length, the axial location of the reverser, and the type of fan inlet. It was shown that significant total and static pressure distortions were produced in the fan aft duct, and that some configurations induced a static pressure distortion at the fan face. The amount of flow passed by the fan and the level of the flow distortions were dependent upon all the variables tested.
Document ID
19750016673
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Dietrich, D. A. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 3, 2013
Publication Date
June 1, 1975
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NASA-TM-X-3247
E-8223
Accession Number
75N24745
Funding Number(s)
PROJECT: RTOP 505-05
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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