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A method for obtaining temperature profiles for solid propellant motor exhaust streams.Theoretical analysis of heat transfer in solid propellant rocket exhaust plumes by use of temperature probe located in plume environment
Document ID
19670032372
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Mcgee, R. S.
Say, M. B.
Date Acquired
August 3, 2013
Publication Date
October 1, 1966
Subject Category
Instrumentation And Photography
Accession Number
67A11101
Funding Number(s)
CONTRACT_GRANT: NAS8-11760
Distribution Limits
Public
Copyright
Other
Keywords
SOLID PROPELLANT ROCKET ENGINE
TEMPERATURE PROBE
ROCKET EXHAUST

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