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Effect of nonlifting empennage surfaces on single-engine afterbody/nozzle drag at Mach numbers from 0.5 to 2.2The effect of empennage interference on the drag characteristics of a model with a single engine fighter aft end with convergent-divergent nozzles was studied. The dry and maximum afterburning nozzle power settings were investigated. A high pressure air system was used to provide jet total pressure ratios up to 20.0. In an attempt to quantify and reduce adverse empennage interference and decrease aft-end drag, several empennage arrangements (variable tail surface location), contour bump configurations, and locally contoured afterbodies were investigated. The results of the investigation indicate that empennage interference effects can be significant at transonic and supersonic speeds. The most effective means of reducing adverse empennage interference is the proper relocation of individual tail surfaces. The aft or conventional empennage arrangement produced the highest aft-end drag at all conditions investigated.
Document ID
19770012066
Acquisition Source
Legacy CDMS
Document Type
Other - NASA Technical Note (TN)
Authors
Berrier, B. L. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 3, 2013
Publication Date
February 1, 1977
Subject Category
Aerodynamics
Report/Patent Number
L-11014
NASA-TN-D-8326
Accession Number
77N19010
Funding Number(s)
PROJECT: RTOP 505-04-11-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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