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Flight test results from a supercritical mission adaptive wing with smooth variable camberResults from the wing surface and boundary layer pressures, buffet studies and flight deflection measurement system for the advanced fighter technology integration F-111 mission adaptive wing program are presented. The different aerodynamic technologies studied on the aircraft, and their relationship with each other are described. The wingtip twist measurements provide an insight as to how dynamic pressures for positive normal accelerations affect the wingtip pressure profiles.
Document ID
19930027277
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Powers, Sheryll G.
(NASA Hugh L. Dryden Flight Research Facility Edwards, CA, United States)
Webb, Lannie D.
(NASA Hugh L. Dryden Flight Research Facility Edwards, CA, United States)
Friend, Edward L.
(NASA Hugh L. Dryden Flight Research Facility Edwards, CA, United States)
Lokos, William A.
(NASA Flight Research Center Edwards, CA, United States)
Date Acquired
August 15, 2013
Publication Date
January 1, 1992
Publication Information
Publication: In: AIAA Biennial Flight Test Conference, 6th, Hilton Head Island, SC, Aug. 24-26, 1992, Technical Papers (A93-11251 01-05)
Publisher: American Institute of Aeronautics and Astronautics
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
AIAA PAPER 92-4101
Accession Number
93A11274
Distribution Limits
Public
Copyright
Other

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