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Static internal performance of a single-engine onaxisymmetric-nozzle vaned-thrust-reverser design with thrust modulation capabilitiesAn investigation has been conducted at wind-off conditions in the stati-test facility of the Langley 16-Foot Transonic Tunnel. The tests were conducted on a single-engine reverser configuration with partial and full reverse-thrust modulation capabilities. The reverser design had four ports with equal areas. These ports were angled outboard 30 deg from the vertical impart of a splay angle to the reverse exhaust flow. This splaying of reverser flow was intended to prevent impingement of exhaust flow on empennage surfaces and to help avoid inlet reingestion of exhaust gas when the reverser is integrated into an actual airplane configuration. External vane boxes were located directly over each of the four ports to provide variation of reverser efflux angle from 140 deg to 26 deg (measured forward from the horizontal reference axis). The reverser model was tested with both a butterfly-type inner door and an internal slider door to provide area control for each individual port. In addition, main nozzle throat area and vector angle were varied to examine various methods of modulating thrust levels. Other model variables included vane box configuration (four or six vanes per box), orientation of external vane boxes with respect to internal port walls (splay angle shims), and vane box sideplates. Nozzle pressure ratio was varied from 2.0 approximately 7.0.
Document ID
19860010877
Document Type
Technical Publication (TP)
Authors
Leavitt, L. D. (NASA Langley Research Center Hampton, VA, United States)
Burley, J. R., II (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 5, 2013
Publication Date
December 1, 1985
Subject Category
AERODYNAMICS
Report/Patent Number
L-15991
NASA-TP-2519
NAS 1.60:2519
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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