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Subsonic/supersonic aerodynamic characteristics for a tactical supercruiserA series of cooperative NASA-Langley/Boeing experimental investigations have been conducted to determine the aeropropulsive characteristics of an advanced tactical fighter designed for supersonic cruise. These investigations were conducted in the Langley 16-Foot Transonic and Lewis 10 x 10-Foot Supersonic Wind Tunnels at Mach numbers from 0.60 to 2.47. This fighter is a Mach 2.0, 49,000 pound class vehicle that features a close-coupled canard and underwing propulsion units that utilize multifunction two-dimensional exhaust nozzles. Tests were conducted to determine the basic aerodynamic characteristics of the configuration with flow-through nacelles in which the spillage effects of representative inlets were measured. The effects of thrust-induced forces on overall aerodynamic performance were evaluated with a series of multifunction nozzles installed on air-powered nacelles. An axisymmetric nozzle configuration was also tested to obtain comparative aeropropulsive performance. Trim aerodynamic characteristics for the flow-through and powered configurations and the effect of thrust vectoring at subsonic speeds are presented.
Document ID
19840061408
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Capone, F. J.
(NASA Langley Research Center Hampton, VA, United States)
Bare, E. A.
(NASA Langley Research Center Transonic Aerodynamics Div., Hampton, VA, United States)
Hollenback, D.
(NASA Langley Research Center Hampton, VA, United States)
Hutchison, R.
(Boeing Military Airplane Co. Seattle, WA, United States)
Date Acquired
August 12, 2013
Publication Date
August 1, 1984
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 84-2192
Accession Number
84A44195
Distribution Limits
Public
Copyright
Other

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