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An experimental investigation on unit Reynolds number and bluntness effects on boundary-layer transition for a 10 deg half- angle cone at M infinity equals 7Reynolds number and nose bluntness effects on boundary layer transition for hypersonic half angle cone
Document ID
19690030819
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Fischer, M. C. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 2, 2013
Publication Date
June 1, 1969
Subject Category
Fluid Mechanics
Report/Patent Number
NASA-TM-X-61906
Report Number: NASA-TM-X-61906
Accession Number
69N40204
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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