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Performance and noise of a low pressure ratio variable pitch fan designed for general aviation applications

Author
Metzger, F. B.
Published
Jan 31, 1980.
Physical Description
1 electronic document
Additional Creators
Mccolgan, C. J. and Menthe, R. W.
Online Version

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Unclassified, Unlimited, Publicly available.
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Summary
A limited study has been conducted to establish the performance and noise characteristics of a low design tip speed (168 m/s, 550 ft/sec) low pressure ratio (1.04) variable pitch fan which was tested in the Langley 30 X 60 tunnel. This fan was designed for minimum noise when installed in the tail mount location of a twin engine aircraft which normally has both nose and tail mounted propulsors. Measurements showed the fan noise to be very close to predictions made during the design of the fan and extremely low in level (65 dBA at 1000 ft) with no acoustic treatment. This is about 8 dB lower than the unshrouded 2 blade propeller normally used in this installation. On the basis of tests conducted during this program, it appears that this level could be further reduced by 2 dBA if optimized acoustic treatments were installed in the fan duct. Even the best of the shrouded propellers tested previously were 7 dB higher in level than the Q-Fan without acoustic treatment. It was found that the cruise performance of this fan was within 5% of the predicted efficiency of 72%. Evaluation of the performance data indicated that disturbances in the inflow to the fan were the probable cause of the reduced performance.
Other Subject(s)
Collection
NASA Technical Reports Server (NTRS) Collection.
Note
Document ID: 19810018561.
Accession ID: 81N27099.
NASA-CR-159246.
Terms of Use and Reproduction
No Copyright.
View MARC record | catkey: 15718652