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Experimental results of a deflected thrust V/STOL nozzle research programFour deflected thrust nozzle concepts, designed to operate at the low pressure ratio typical of high bypass-ratio turbofan engines for medium speed (subsonic) V/STOL aircraft, were studied. Maps of overall performance characteristics and exit velocity distributions are used to highlight similarities and differences between the four concepts. Analytically determined secondary flows at the exit of a 90 deg circular pipe bend are compared with the experimental results from the more complex three dimensional geometries. The relative impact of total-pressure losses and secondary flows on nozzle thrust coefficient is addressed by numerical integration of exit velocity measurements. Previously announced in STAR as N83-25657
Document ID
19830060882
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Burstadt, P. L.
(NASA Lewis Research Center Cleveland, OH, United States)
Johns, A. L.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
August 11, 2013
Publication Date
January 1, 1983
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 83-0170
Accession Number
83A42100
Distribution Limits
Public
Copyright
Other

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