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Effects of afterbody boattail design and empennage arrangement on aeropropulsive characteristics of a twin-engine fighter model at transonic speedsThe effects of empennage arrangement and afterbody boattail design of nonaxisymmetric nozzles on the aeropropulsive characteristics of a twin-engine fighter-type model have been determined in an investigation conducted in the Langley 16-Foot Transonic Tunnel. Three nonaxisymmetric and one twin axisymmetric convergent-divergent nozzle configurations were tested with three different tail arrangements: a two-tail V-shaped arrangement; a staggered, conventional three-tail arrangement; and a four-tail arrangement similar to that on the F-18. Two of the nonaxisymmetric nozzles were also vectorable. Tests were conducted at Mach numbers from 0.60 to 1.20 over an angle-of-attack range from -3 deg to 9 deg. Nozzle pressure ratio was varied from 1 (jet off) to approximately 12, depending on Mach number. Results indicate that at design nozzle pressure ratio, the medium aspect ratio nozzle (with equal boattail angles on the nozzle sidewalls and upper and lower flaps) had the lowest zero angle of attack drag of the nonaxisymmetric nozzles for all tail configurations at subsonic Mach numbers. The drag levels of the twin axisymmetric nozzles were competitive with those of the medium-aspect-ratio nozzle at subsonic Mach number.
Document ID
19870012440
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Bangert, Linda S. (NASA Langley Research Center Hampton, VA, United States)
Leavitt, Laurence D. (NASA Langley Research Center Hampton, VA, United States)
Reubush, David E. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 5, 2013
Publication Date
June 1, 1987
Subject Category
Aerodynamics
Report/Patent Number
NAS 1.60:2704
NASA-TP-2704
L-16227
Accession Number
87N21873
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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