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Static investigation of circular-to-rectangular transition ducts for high-aspect-ratio nonaxisymmetric nozzlesAn investigation was conducted in the static-test facility of the Langley 16-Foot Transonic Tunnel to determine the internal performance of a high-aspect-ratio nonaxisymmetric nozzle with five circular-to-rectangular transition ducts of varying design. Nozzle pressure ratio was varied from 1.5 to 5.3, and nozzle performance parameters were recorded.
Document ID
19860013105
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Burley, J. R., II (NASA Langley Research Center Hampton, VA, United States)
Bangert, L. S. (NASA Langley Research Center Hampton, VA, United States)
Carlson, J. R. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 5, 2013
Publication Date
March 1, 1986
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NASA-TP-2534
L-15874
NAS 1.60:2534
Accession Number
86N22576
Funding Number(s)
PROJECT: RTOP 505-40-90-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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