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Static investigation of two STOL nozzle concepts with pitch thrust-vectoring capabilityA static investigation of the internal performance of two short take-off and landing (STOL) nozzle concepts with pitch thrust-vectoring capability has been conducted. An axisymmetric nozzle concept and a nonaxisymmetric nozzle concept were tested at dry and afterburning power settings. The axisymmetric concept consisted of a circular approach duct with a convergent-divergent nozzle. Pitch thrust vectoring was accomplished by vectoring the approach duct without changing the nozzle geometry. The nonaxisymmetric concept consisted of a two dimensional convergent-divergent nozzle. Pitch thrust vectoring was implemented by blocking the nozzle exit and deflecting a door in the lower nozzle flap. The test nozzle pressure ratio was varied up to 10.0, depending on model geometry. Results indicate that both pitch vectoring concepts produced resultant pitch vector angles which were nearly equal to the geometric pitch deflection angles. The axisymmetric nozzle concept had only small thrust losses at the largest pitch deflection angle of 70 deg., but the two-dimensional convergent-divergent nozzle concept had large performance losses at both of the two pitch deflection angles tested, 60 deg. and 70 deg.
Document ID
19860014088
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Mason, M. L. (NASA Langley Research Center Hampton, VA, United States)
Burley, J. R., II (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 5, 2013
Publication Date
April 1, 1986
Subject Category
Aerodynamics
Report/Patent Number
NASA-TP-2559
NAS 1.60:2559
L-165052
Accession Number
86N23559
Funding Number(s)
PROJECT: RTOP 505-62-91-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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