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Experimental shock-tube investigation of conditions behind incident and reflected shocks in air for shock Mach numbers between 8.5 and 16.5.Incident and reflected shocks from laminar and turbulent boundary layers measured over various Mach numbers
Document ID
19670059042
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Dunn, M. G.
Date Acquired
August 3, 2013
Publication Date
January 1, 1967
Subject Category
Fluid Mechanics
Accession Number
67A37771
Funding Number(s)
CONTRACT_GRANT: NAS5-9978
Distribution Limits
Public
Copyright
Other
Keywords
WAVE REFLECTION
TURBULENT BOUNDARY LAYER
LAMINAR BOUNDARY LAYER
MACH NUMBER
SHOCK WAVE

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