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Aerodynamic Characteristics of a Supersonic Fighter Aircraft Model at Mach 0.40 to 2.47The aerodynamic characteristics of an advanced twin-engine fighter aircraft designed for supersonic cruise have been studied in the Langley 16-Foot Transonic Tunnel and the Lewis 10- by 10-Foot Supersonic Tunnel. The objective of this investigation was to establish an aerodynamic data base for the configuration with flow-through nacelles and representative inlets. The use of a canard for trim and the effects of fairing over the inlets were assessed. Comparisons between experimental and theoretical results were also made. The theoretical results were determined by using a potential vortex lift code for subsonic speeds and a linear aerodynamic code for supersonic speeds. This investigation was conducted at Mach numbers from 0.40 to 2.47, at angles of attack from 0 deg to about 20 deg, and at inlet capture ratios of about 0.5 to 1.4.
Document ID
19860014090
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Capone, F. J.
(NASA Langley Research Center Hampton, VA, United States)
Bare, E. A.
(NASA Langley Research Center Hampton, VA, United States)
Arbiter, D.
(George Washington Univ. Hampton, Va., United States)
Date Acquired
September 5, 2013
Publication Date
April 1, 1986
Subject Category
Aerodynamics
Report/Patent Number
NASA-TP-2580
L-16017
NAS 1.60:2580
Accession Number
86N23561
Funding Number(s)
PROJECT: RTOP 505-43-90-07
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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