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Supersonic aerodynamic characteristics of an advanced F-16 derivative aircraft configurationA supersonic wind tunnel investigation was conducted in the NASA Langley Unitary Plan Wind Tunnel on an advanced derivative configuration of the United States Air Force F-16 fighter. Longitudinal and lateral directional force and moment data were obtained at Mach numbers of 1.60 to 2.16 to evaluate basic performance parameters and control effectiveness. The aerodynamic characteristics for the F-16 derivative model were compared with the data obtained for the F-16C model and also with a previously tested generic wing model that features an identical plan form shape and similar twist distribution.
Document ID
19930022544
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Fox, Mike C. (Vigyan Research Associates, Inc. Hampton, VA., United States)
Forrest, Dana K. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 6, 2013
Publication Date
July 1, 1993
Subject Category
Aerodynamics
Report/Patent Number
NASA-TP-3355
L-17143
NAS 1.60:3355
Accession Number
93N31733
Funding Number(s)
PROJECT: RTOP 505-59-30-01
CONTRACT_GRANT: NAS1-18585
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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