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APPLICATION OF TRANSTABILITY CONCEPT TO FLUTTER OF FINITE PANELS AND EXPERIMENTAL RESULTSExperiment and theory of supersonic flutter in panels - length/width and stress ratios to prevent flutter of various thicknesses at mach 3
Document ID
19630011175
Acquisition Source
Legacy CDMS
Document Type
Other - NASA Technical Note (TN)
Authors
Dixon, S. C. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 2, 2013
Publication Date
September 1, 1963
Subject Category
Thermodynamics And Combustion
Report/Patent Number
NASA-TN-D-1948
Report Number: NASA-TN-D-1948
Accession Number
63N21055
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
PANEL FLUTTER
SUPERSONIC FLUTTER
STRESS RATIO
BUCKLING

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