Editing Thrust vectoring (section)

=== Definitions ===
[[File:3 three thrust-vectoring aircraft.jpg|thumb|Three experimental thrust vectoring aircraft in flight; from left to right, [[F-18 HARV]], [[X-31]], and [[F-16 VISTA|F-16 MATV]]]]
; Axisymmetric:  Nozzles with circular exits.
; Conventional aerodynamic flight control (CAFC): Pitch, yaw-pitch, yaw-pitch-roll or any other combination of aircraft control through aerodynamic deflection using rudders, flaps, elevators and/or ailerons.
; Converging-diverging nozzle (C-D): Generally used on supersonic jet aircraft where nozzle pressure ratio (npr) > 3. The engine exhaust is expanded through a converging section to achieve Mach 1 and then expanded through a diverging section to achieve supersonic speed at the exit plane, or less at low npr.<ref name="aiaa3923">"Nozzle Selection and Design Criteria" Gambell, Terrell, DeFrancesco, AIAA 2004-3923</ref>
; Converging nozzle: Generally used on subsonic and transonic jet aircraft where npr < 3. The engine exhaust is expanded through a converging section to achieve Mach 1 at the exit plane, or less at low npr.<ref name="aiaa3923"/>
; Effective Vectoring Angle: The average angle of deflection of the jet stream centreline at any given moment in time.
; Fixed nozzle:  A thrust-vectoring nozzle of invariant geometry or one of variant geometry maintaining a constant geometric area ratio, during vectoring. This will also be referred to as a civil aircraft nozzle and represents the nozzle thrust vectoring control applicable to passenger, transport, cargo and other subsonic aircraft.
; Fluidic thrust vectoring: The manipulation or control of the exhaust flow with the use of a secondary air source, typically bleed air from the engine compressor or fan.<ref name="fluidic">"Experimental Study of an Axisymmetric Dual Throat Fluidic Thrust Vectoring Nozzle for Supersonic Aircraft application" Flamme, Deere, Mason, Berrier, Johnson, https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20070030933.pdf {{Webarchive|url=https://web.archive.org/web/20170815115330/https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20070030933.pdf |date=2017-08-15 }}</ref>
; Geometric vectoring angle:  Geometric centreline of the nozzle during vectoring. For those nozzles vectored at the geometric throat and beyond, this can differ considerably from the effective vectoring angle.
; Three-bearing swivel duct nozzle (3BSD<ref name="aiaa1"/>): Three angled segments of engine exhaust duct rotate relative to one another about duct centreline to produce nozzle thrust axis pitch and yaw.<ref name="code1">{{cite web|url=http://www.codeonemagazine.com/article.html?item_id=137|title=F-35B Lightning II Three-Bearing Swivel Nozzle - Code One Magazine|website=codeonemagazine.com|access-date=2015-02-01|archive-date=2014-07-19|archive-url=https://web.archive.org/web/20140719223459/http://www.codeonemagazine.com/article.html?item_id=137|url-status=live}}</ref>
; Three-dimensional (3-D): Nozzles with multi-axis or pitch and yaw control.<ref name="spain"/>
; Thrust vectoring (TV):  The deflection of the jet away from the body-axis through the implementation of a flexible nozzle, flaps, paddles, auxiliary fluid mechanics or similar methods.
; Thrust-vectoring flight control (TVFC):  Pitch, yaw-pitch, yaw-pitch-roll, or any other combination of aircraft control through deflection of thrust generally issuing from an air-breathing turbofan engine.
; Two-dimensional (2-D):  Nozzles with square or rectangular exits. In addition to the geometrical shape 2-D can also refer to the degree-of-freedom (DOF) controlled which is single axis, or pitch-only, in which case round nozzles are included.<ref name="spain"/>
; Two-dimensional converging-diverging (2-D C-D):  Square, rectangular, or round supersonic nozzles on fighter aircraft with pitch-only control.
; Variable nozzle:  A thrust-vectoring nozzle of variable geometry maintaining a constant, or allowing a variable, effective nozzle area ratio, during vectoring. This will also be referred to as a military aircraft nozzle as it represents the nozzle thrust vectoring control applicable to fighter and other supersonic aircraft with afterburning. The convergent section may be fully controlled with the divergent section following a pre-determined relationship to the convergent throat area.<ref name="spain"/> Alternatively, the throat area and the exit area may be controlled independently, to allow the divergent section to match the exact flight condition.<ref name="spain"/>