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Incipient separation of a turbulent boundary layer at high Reynolds number in two- dimensional supersonic flow over a compression cornerMach number effects on pressure caused incipient separation of turbulent boundary layer in two dimensional supersonic corner flow
Document ID
19690027911
Document Type
Contractor Report (CR)
Authors
Roshko, A. (McDonnell-Douglas Astronautics Co. Santa Monica, CA, United States)
Thomke, G. J. (McDonnell-Douglas Astronautics Co. Santa Monica, CA, United States)
Date Acquired
September 2, 2013
Publication Date
January 31, 1969
Subject Category
Fluid Mechanics
Report/Patent Number
DAC-59819
NASA-CR-73308
Accession Number
69N37289
Funding Number(s)
CONTRACT_GRANT: NAS7-589
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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