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Effects of installation of F101 DFE exhaust nozzles on the afterbody-nozzle characteristics of the F-14 airplaneA wind-tunnel investigation was conducted to determine the effects of F101 DFE (derivative fighter engine) nozzle axial positioning on the afterbody-nozzle longitudinal aerodynamic characteristics of the F-14 airplane. The model was tested in the Langley 16-Foot Transonic Tunnel at Mach numbers from 0.7 to 1.25 and angles of attack from about -2 to 6 degrees. Compressed air was used to simulate nozzle exhaust flow at jet total-pressure ratios from 1 (jet off) to about 8. The results of the investigation show that for subsonic Mach numbers the intermediate cruise nozzle position of the three positions tested resulted in the lowest drag.
Document ID
19820011307
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Reubush, D. E. (NASA Langley Research Center Hampton, VA, United States)
Carlson, J. R. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 4, 2013
Publication Date
March 1, 1982
Subject Category
Aerodynamics
Report/Patent Number
NASA-TM-83250
L-14895
Accession Number
82N19181
Funding Number(s)
PROJECT: RTOP 505-31-43-04
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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