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Investigation of installation effects on twin-engine convergent-divergent nozzlesAn investigation was conducted in the Langley 16-Foot Transonic Tunnel to determine installation effects on convergent-divergent nozzles applicable to twin-engine reduced-power supersonic cruise aircraft. Tests were conducted at Mach numbers from 0.50 to 1.20, angles of attack from -5 deg to 9 deg, and at nozzle pressure ratios from jet off (1.0) to 8.0. The effects of empennage arrangement, nozzle length, and afterbody closure on total and component drag coefficients were investigated.
Document ID
19840005084
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Bare, E. A. (NASA Langley Research Center Hampton, VA, United States)
Berrier, B. L. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 4, 2013
Publication Date
November 1, 1983
Subject Category
Aerodynamics
Report/Patent Number
NASA-TP-2205
L-15609
NAS 1.60:2205
Accession Number
84N13152
Funding Number(s)
PROJECT: RTOP 505-43-23-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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