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Static investigation of several yaw vectoring concepts on nonaxisymmetric nozzlesA test has been conducted in the static test facility of the Langley 16-Foot Transonic Tunnel to determine the flow-turning capability and the effects on nozzle internal performance of several yaw vectoring concepts. Nonaxisymmetric convergent-divergent nozzles with throat areas simulating dry and afterburning power settings and single expansion ramp nozzles with a throat area simulating a dry power setting were modified for yaw thrust vectoring. Forward-thrust and pitch-vectored nozzle configurations were tested with each yaw vectoring concept. Four basic yaw vectoring concepts were investigated on the nonaxisymmetric convergent-divergent nozzles: (1) translating sidewall; (2) downstream (of throat) flaps; (3) upstream (of throat) port/flap; and (4) powered rudder. Selected combinations of the rudder with downstream flaps or upstream port/flap were also tested. A single yaw vectoring concept, post-exit flaps, was investigated on the single expansion ramp nozzles. All testing was conducted at static (no external flow) conditions and nozzle pressure ratios varied from 2.0 up to 10.0.
Document ID
19850020612
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Mason, M. L.
(NASA Langley Research Center Hampton, VA, United States)
Berrier, B. L.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 5, 2013
Publication Date
June 1, 1985
Subject Category
Aerodynamics
Report/Patent Number
L-15890
NASA-TP-2432
NAS 1.60:2432
Accession Number
85N28924
Funding Number(s)
PROJECT: RTOP 505-40-90
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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