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Unit Reynolds number effects on boundary-layer transition at Mach 6.Boundary layer transition measurement on windward side of flat plate in hypersonic wind tunnel, discussing unit Reynolds number effects at Mach 6
Document ID
19680046142
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Hopkins, E. J.
Keener, E. R.
Date Acquired
August 4, 2013
Publication Date
May 1, 1968
Subject Category
Fluid Mechanics
Accession Number
68A27114
Distribution Limits
Public
Copyright
Other

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