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An experimental study of tip shape effects on the flutter of aft-swept, flat-plate wingsThe effects of tip chord orientation on wing flutter are investigated experimentally using six cantilever-mounted, flat-plate wing models. Experimentally determined flutter characteristics of the six models are presented covering both the subsonic and transonic Mach number ranges. While all models have a 60 degree leading edge sweep, a 40.97 degree trailing edge sweep, and a root chord of 34.75 inches, they are subdivided into two series characterized by a higher aspect ratio and a lower aspect ratio. Each series is made up of three models with tip chord orientations which are parallel to the free-stream flow, perpendicular to the model mid-chord line, and perpendicular to the free-stream flow. Although planform characteristics within each series of models are held constant, structural characteristics such as mode shapes and natural frequencies are allowed to vary.
Document ID
19900013239
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Dansberry, Bryan E. (NASA Langley Research Center Hampton, VA, United States)
Rivera, Jose A., Jr. (NASA Langley Research Center Hampton, VA, United States)
Farmer, Moses G. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 6, 2013
Publication Date
June 1, 1990
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
L-16638
NASA-TM-4180
NAS 1.15:4180
Accession Number
90N22555
Funding Number(s)
PROJECT: RTOP 505-63-21-09
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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