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KC-135A Winglet Flight Flutter ProgramThe evaluation techniques, results and conclusions for the flight flutter testing conducted on a KC-135A airplane configured with and without winglets are discussed. Test results are presented for the critical symmetric and antisymmetric modes for a fuel distribution that consisted of 10,000 pounds in each wing main tank and empty reserve tanks. The results indicated that a lightly damped oscillation was experienced for a winglet configuration of a 0 deg cant and -4 deg incidence. The effects of cant and incidence angle variation on the critical modes are also discussed. Lightly damped oscillations were not encountered for any other winglet cant and incidence angles tested.
Document ID
19840019624
Document Type
Conference Paper
Authors
Kehoe, M. W.
(NASA Hugh L. Dryden Flight Research Center Edwards, CA, United States)
Date Acquired
August 12, 2013
Publication Date
December 1, 1982
Publication Information
Publication: NASA. Dryden Flight Research Facility KC-135 Winglet Program Rev.
Subject Category
Aerodynamics
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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