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Experimental investigation of orthotropic panel flutter at arbitrary yaw angles, and comparison with theoryFlutter characteristics for yaw angles between 15 deg and 90 deg were determined experimentally for two types of corrugation-stiffened panels: those with weak twisting stiffness and those with strong twisting stiffness. By mounting the panels on a remotely controlled turntable, good definition of the flutter boundaries was obtained by rotating the panels into and out of flutter. Flutter tests were conducted at M = 2 and M = 1.6. Before testing, vibration tests and analyses were also performed. The experimental flutter data is compared with flutter theory for orthotropic panels utilizing quasi-steady aerodynamics. Five different corrugated panels were tested consisting of one single skin panel having a length-to-width ratio of 5 on clamped supports and four different square double skin panels on discrete flexible supports. The investigation indicated that flutter speed for corrugated panels is highly dependent on yaw angle. Reasonable flutter correlation between analysis and test was obtained for moderate yaw angles, but extreme sensitivity to structural parameters made the correlation at large yaw angles uncertain.
Document ID
19730015183
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Shyprykevich, P.
(Grumman Aerospace Corp. Bethpage, NY, United States)
Date Acquired
September 2, 2013
Publication Date
May 1, 1973
Publication Information
Publisher: NASA
Subject Category
Structural Mechanics
Report/Patent Number
NASA-CR-2265
Accession Number
73N23910
Funding Number(s)
CONTRACT_GRANT: NAS1-10635
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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