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Wingtip vortex turbine investigation for vortex energy recoveryA flight test investigation has been conducted to determine the performance of wingtip vortex turbines and their effect on aircraft performance. The turbines were designed to recover part of the large energy loss (induced drag) caused by the wingtip vortex. The turbine, driven by the vortex flow, reduces the strength of the vortex, resulting in an associated induced drag reduction. A four-blade turbine was mounted on each wingtip of a single-engine, T-tail, general aviation airplane. Two sets of turbine blades were tested, one with a 15' twist (washin) and one with no twist. Th power recovered by the turbine and the installed drag increment were measured. A trade-off between turbine power and induced drag reduction was found to be a function of turbine blade incidence angle. This test has demonstrated that the wingtip vortex turbine is an attractive alternate, as well as an emergency, power source.
Document ID
19910063991
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Abeyounis, William K.
(NASA Langley Research Center Hampton, VA, United States)
Patterson, James C., Jr.
(NASA Langley Research Center Hampton, VA, United States)
Stough, H. P., III
(NASA Langley Research Center Hampton, VA, United States)
Wunschel, Alfred J.
(USAF Wright-Patterson AFB, OH, United States)
Curran, Patrick D.
(Sundstrand Aviation Rockford, IL, United States)
Date Acquired
August 14, 2013
Publication Date
September 1, 1990
Subject Category
Aerodynamics
Report/Patent Number
SAE PAPER 901936
Accession Number
91A48614
Distribution Limits
Public
Copyright
Other

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