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Thrust-induced effects on subsonic longitudinal aerodynamic characteristics of a vectored-engine-over-wing configurationAn investigation was conducted in the Langley 4 by 7 Meter Tunnel of the thrust induced effects on the longitudinal aerodynamic characteristics of a vectored-engine-over-wing fighter aircraft. The investigation was conducted at Mach numbers from 0.14 to 0.17 over an angle-of-attack range from -2 deg to 26 deg. The major model variables were the spanwise blowing nozzle sweep angle and main nozzle vector angle along with trailing edge, flap deflections. The overall thrust coefficient (main and spanwise nozzles) was varied from 0 (jet off) to 2.0. The results indicate that the thrust-induced effects from the main nozzle alone were small and mainly due to boundary-layer control affecting a small area behind the nozzle. When the spanwise blowing nozzles were included, the induced effects were larger than the main nozzle alone and were due to both boundary layer control and induced circulation lift. No leading edge vortex effects were evident.
Document ID
19840005095
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Quinto, P. F. (NASA Langley Research Center Hampton, VA, United States)
Paulson, J. W., Jr. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 4, 2013
Publication Date
December 1, 1983
Subject Category
Aerodynamics
Report/Patent Number
NASA-TP-2228
NAS 1.60:2228
L-15629
Accession Number
84N13163
Funding Number(s)
PROJECT: RTOP 505-43-23-04
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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