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Effect of empennage location on twin-engine afterbody-nozzle aerodynamic characteristics at Mach Numbers from 0.6 to 1.2The Langley 16-foot transonic tunnel was used to determine the effects of several empennage and afterbody parameters on the aft-end aerodynamic characteristics of a twin-engine fighter-type configuration. Model variables were as follows: horizontal tail axial location and incidence, vertical tail axial location and configuration (twin- versus single-tail arrangements), tail booms, and nozzle power setting. Tests were conducted over a Mach number range from 0.6 to 1.2 and over an angle-of-attack from -2 deg to 10 deg. Jet total-pressure ratio was varied from jet off to approximately 10.0.
Document ID
19830017395
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Leavitt, L. D. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 4, 2013
Publication Date
May 1, 1983
Subject Category
Aerodynamics
Report/Patent Number
NASA-TP-2116
NAS 1.60:2116
L-15527
Accession Number
83N25666
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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