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Calculation by a finite difference method of supersonic turbulent boundary layers with tangential slot injectionFinite difference calculation based on eddy diffusivity and mixing length flow theory to characterize supersonic turbulent boundary layer with tangential slot injection
Document ID
19710013093
Acquisition Source
Legacy CDMS
Document Type
Other - NASA Technical Note (TN)
Authors
Beckwith, I. E. (NASA Langley Research Center Hampton, VA, United States)
Bushnell, D. M. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 2, 2013
Publication Date
April 1, 1971
Subject Category
Aerodynamics
Report/Patent Number
L-7515
NASA-TN-D-6221
Report Number: L-7515
Report Number: NASA-TN-D-6221
Accession Number
71N22569
Funding Number(s)
CONTRACT_GRANT: 129-01-20-09
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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