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Shock tube instrumentation techniques for study of hypervelocity entry problemsShock tube instrumentation methods for convective heat transfer study and radiative properties of high temperature gas at conditions simulating hypervelocity entry
Document ID
19650010156
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Gruszczynski, J. S. (General Electric Co. Philadelphia, PA, United States)
Rogers, D. A. (General Electric Co. Philadelphia, PA, United States)
Date Acquired
August 2, 2013
Publication Date
September 1, 1964
Subject Category
Thermodynamics And Combustion
Report/Patent Number
NASA-CR-57220
R64SD67
AD-451136
Report Number: NASA-CR-57220
Report Number: R64SD67
Report Number: AD-451136
Accession Number
65N19757
Funding Number(s)
CONTRACT_GRANT: NAS7-100
CONTRACT_GRANT: JPL-950297
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
HYPERVELOCITY
HIGH TEMPERATURE GAS
CONVECTIVE HEAT TRANSFER
ATMOSPHERIC ENTRY
SHOCK TUNNEL

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