NDLI: Static investigation of several yaw vectoring concepts on nonaxisymmetric nozzles

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Static investigation of several yaw vectoring concepts on nonaxisymmetric nozzles

Content Provider	NASA Technical Reports Server (NTRS)
Author	Berrier, B. L. Mason, M. L.
Copyright Year	1985
Description	A 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.
File Size	59219329
Page Count	220
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19850020612
Archival Resource Key	ark:/13960/t0bw2c081
Language	English
Publisher Date	1985-06-01
Access Restriction	Open
Subject Keyword	Aerodynamics Nozzle Geometry Throats Thrust Vector Control Wind Tunnel Tests Convergent-divergent Nozzles Fighter Aircraft Yaw Static Tests Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Technical Report

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