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Orthotropic panel flutter at arbitrary yaw angles - Experiment and correlation with theory.Experimental flutter boundaries were obtained for yaw angles between 15 and 90 deg at Mach numbers 2 and 1.6 for panels mounted on a remotely controlled turntable. Good definition of the flutter boundaries was obtained by rotating the panels into and out of flutter. Two types of specimens were tested: a single-sheet corrugated panel having a length-to-width ratio of 5 on clamped supports, and several square doubly-corrugated panels on various flexible supports. Calculated flutter speeds based on quasi-steady aerodynamics are compared to experimental data.
Document ID
19730032122
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Shyprykevich, P.
(Grumman Aerospace Corp. Bethpage, N.Y., United States)
Sawyer, J. W.
(NASA Langley Research Center Structures Div., Hampton, Va., United States)
Date Acquired
August 7, 2013
Publication Date
January 1, 1973
Subject Category
Structural Mechanics
Report/Patent Number
AIAA PAPER 73-192
Meeting Information
Meeting: Aerospace Sciences Meeting
Location: Washington, DC
Start Date: January 10, 1973
End Date: January 12, 1973
Sponsors: American Institute of Aeronautics and Astronautics
Accession Number
73A16924
Funding Number(s)
CONTRACT_GRANT: NAS1-10635-6
Distribution Limits
Public
Copyright
Other

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