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Static internal performance of a nonaxisymmetric vaned thrust reverser with flow splay capabilityAn investigation was conducted in the Static Test Facility of the Langley 16-Foot Transonic Tunnel on a dual-port, nonaxisymmetric, block-and-turn type thrust reverser model with vane cascades in the reverser ports which turned the flow in the splay direction and aided in turning the flow in the reverse direction. Splaying reverser flow is a method of delaying to lower landing ground roll speeds the reingestion of hot exhaust flow into the inlets. Exhaust flow splay can also help prevent the impingement of hot exhaust gases on the empennage surfaces when the reverser is integrated into an actual airframe. The vane cascades consisted of two sets of perpendicular vanes with a variable number of turning and splay vanes. A skewed vane box was also tested which had only one set of vanes angled to provide both turning and splay. Vane cascades were designed to provide different amounts of flow splay in the top and bottom ports. Inner doors, trim tabs, and an orifice plate all provided means of varying the port area for reverser flow modulation. The outer door position was varied as a means of influencing the flow reverse angle. Nozzle pressure ratio was varied from 1.75 to approximately 6.00.
Document ID
19890018263
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Bangert, Linda S.
(NASA Langley Research Center Hampton, VA, United States)
Leavitt, Laurence D.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 6, 2013
Publication Date
September 1, 1989
Subject Category
Aerodynamics
Report/Patent Number
NAS 1.60:2933
L-16552
NASA-TP-2933
Accession Number
89N27634
Funding Number(s)
PROJECT: RTOP 505-62-71-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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