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Turbulent boundary-layer heat transfer from rapidly accelerating flow of rocket combustion gases and of heated airTurbulent boundary layer heat transfer from fast accelerating flow of rocket exhaust gases and heated air
Document ID
19650013685
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Bartz, D. R. (Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Date Acquired
August 2, 2013
Publication Date
December 1, 1963
Subject Category
Thermodynamics And Combustion
Report/Patent Number
NASA-CR-62615
Accession Number
65N23286
Funding Number(s)
CONTRACT_GRANT: NASW-6
CONTRACT_GRANT: DA-04-495-ORD-18
CONTRACT_GRANT: NAS7-100
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
TURBULENT BOUNDARY LAYER
GAS FLOW
TURBULENT HEAT TRANSFER
EXHAUST GAS
ROCKET EXHAUST

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