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Subsonic and supersonic longitudinal stability and control characteristics of an aft tail fighter configuration with cambered and uncambered wings and uncambered fuselageAn investigation has been made in the Mach number range from 0.20 to 2.16 to determine the longitudinal aerodynamic characteristics of a fighter airplane concept. The configuration concept employs a single fixed geometry inlet, a 50 deg leading-edge-angle clipped-arrow wing, a single large vertical tail, and low horizontal tails. The wing camber surface was optimized in drag due to lift and was designed to be self-trimming at Mach 1.40 and at a lift coefficient of 0.20. An uncambered or flat wing of the same planform and thickness ratio was also tested. However, for the present investigation, the fuselage was not cambered. Further tests should be made on a cambered fuselage version, which attempts to preserve the optimum wing loading on that part of the theoretical wing enclosed by the fuselage.
Document ID
19740023306
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Dollyhigh, S. M. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 3, 2013
Publication Date
August 1, 1974
Subject Category
Aerodynamics
Report/Patent Number
NASA-TM-X-3078
L-9463
Accession Number
74N31419
Funding Number(s)
PROJECT: RTOP 760-67-01-04
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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