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Transition aerodynamics for close-coupled wing-canard configurationA series of wind-tunnel tests have been conducted in the Langley V/STOL tunnel to investigate the low-speed longitudinal aerodynamics of two powered close-coupled wing-canard fighter configurations. A brief review is provided of the high angle-of-attack data for the two wing-canard configurations tested showing the benefits and problem areas of powered lift. A takeoff and landing analysis is presented which defines the area in which a fighter-type aircraft must operate in order to achieve 305-m field lengths. The wing-canard configuration data are analyzed in detail showing the problems of obtaining high lift, high drag, and trimmed moments. Assuming that power will be used to trim the aircraft, data are presented comparing the transition aerodynamics of the wing-canard configuration using a nose jet with several V/STOL configurations.
Document ID
19790035660
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Paulson, J. W., Jr. (NASA Langley Research Center Hampton, VA, United States)
Thomas, J. L. (NASA Langley Research Center Hampton, VA, United States)
Winston, M. M. (NASA Langley Research Center Subsonic-Transonic Aerodynamics Div., Hampton, Va., United States)
Date Acquired
August 9, 2013
Publication Date
January 1, 1979
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 79-0336
Meeting Information
Meeting: American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting
Location: New Orleans, LA
Start Date: January 15, 1979
End Date: January 17, 1979
Sponsors: American Institute of Aeronautics, Astronautics
Accession Number
79A19673
Distribution Limits
Public
Copyright
Other

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