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Static test of a large scale swivel nozzle thrust deflectorExperimental results from a swivel nozzle thrust deflector test program are presented. The deflector was installed behind a 36-inch fan with a tip turbine hot gas drive. The maximum nozzle pressure ratio was 1.2. Nozzle thrust and flow coefficients are presented for a range of vectoring angles. The results are also compared to small scale cold flow test results. The comparison suggests a need for accurate simulation of nozzle entry pressure and temperature profiles on model tests.
Document ID
19790055007
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Federspiel, J. F. (Rockwell International Corp. Columbus, Ohio, United States)
Date Acquired
August 9, 2013
Publication Date
June 1, 1979
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
AIAA PAPER 79-1285
Report Number: AIAA PAPER 79-1285
Meeting Information
Meeting: AIAA, SAE, and ASME, Joint Propulsion Conference
Location: Las Vegas, NV
Start Date: June 18, 1979
End Date: June 20, 1979
Sponsors: AIAA, ASME, SAE
Accession Number
79A39020
Distribution Limits
Public
Copyright
Other

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