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Static internal performance of a thrust vectoring and reversing two-dimensional convergent-divergent nozzle with an aft flapThe static internal performance of a multifunction nozzle having some of the geometric characteristics of both two-dimensional convergent-divergent and single expansion ramp nozzles has been investigated in the static-test facility of the Langley 16-Foot Transonic Tunnel. The internal expansion portion of the nozzle consisted of two symmetrical flat surfaces of equal length, and the external expansion portion of the nozzle consisted of a single aft flap. The aft flap could be varied in angle independently of the upper internal expansion surface to which it was attached. The effects of internal expansion ratio, nozzle thrust-vector angle (-30 deg. to 30 deg., aft flap shape, aft flap angle, and sidewall containment were determined for dry and afterburning power settings. In addition, a partial afterburning power setting nozzle, a fully deployed thrust reverser, and four vertical takeoff or landing nozzle, configurations were investigated. Nozzle pressure ratio was varied up to 10 for the dry power nozzles and 7 for the afterburning power nozzles.
Document ID
19860014089
Document Type
Technical Publication (TP)
Authors
Re, R. J.
(NASA Langley Research Center Hampton, VA, United States)
Leavitt, L. D.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 5, 2013
Publication Date
April 1, 1986
Subject Category
Aerodynamics
Report/Patent Number
NAS 1.60:2549
NASA-TP-2549
L-16025
Funding Number(s)
PROJECT: RTOP 505-43-90-07
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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