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Experimental flutter study of a wing-fuselage configuration at a mach number of 15.4 and comparison with theoryHelium flow at hypersonic speed used to calculate hypersonic flutter data on low aspect ratio, flexible, wing-fuselage configuration
Document ID
19650026234
Acquisition Source
Legacy CDMS
Document Type
Other - NASA Technical Note (TN)
Authors
Goetz, R. C. (NASA Langley Research Center Hampton, VA, United States)
Sewall, J. L. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 2, 2013
Publication Date
October 1, 1965
Subject Category
Structural Mechanics
Report/Patent Number
NASA-TN-D-3046
Report Number: NASA-TN-D-3046
Accession Number
65N35835
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
LOW ASPECT RATIO WING
HYPERSONIC FLOW
WING-FUSELAGE COMBINATION
HELIUM
FLUTTER ANALYSIS
FLEXIBLE WING

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