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Forward-swept wing configuration designed for high maneuverability by use of a transonic computational methodA transonic computational analysis method and a transonic design procedure have been used to design the wing and the canard of a forward-swept-wing fighter configuration for good transonic maneuver performance. A model of this configuration was tested in the Langley 16-Foot Transonic Tunnel. Oil-flow photographs were obtained to examine the wind flow patterns at Mach numbers from 0.60 to 0.90. The transonic theory gave a reasonably good estimate of the wing pressure distributions at transonic maneuver conditions. Comparison of the forward-swept-wing configuration with an equivalent aft-swept-wing-configuration showed that, at a Mach number of 0.90 and a lift coefficient of 0.9, the two configurations have the same trimmed drag. The forward-swept wing configuration was also found to have trimmed drag levels at transonic maneuver conditions which are comparable to those of the HiMAT (highly maneuverable aircraft technology) configuration and the X-29 forward-swept-wing research configuration. The configuration of this study was also tested with a forebody strake.
Document ID
19870002269
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Mann, M. J. (NASA Langley Research Center Hampton, VA, United States)
Mercer, C. E. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 5, 2013
Publication Date
November 1, 1986
Subject Category
Aerodynamics
Report/Patent Number
NASA-TP-2628
L-16120
NAS 1.60:2628
Accession Number
87N11702
Funding Number(s)
PROJECT: RTOP 505-61-71-03
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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