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A new technique for simulating rocket engine flow for study of base heating problems.Short duration technique providing simulation of thermodynamic properties and composition of exhaust products of liquid and solid propellant rocket engines
Document ID
19660061353
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Wilson, H. B., Jr.
Date Acquired
August 3, 2013
Publication Date
September 1, 1966
Subject Category
Facilities, Research, And Support
Report/Patent Number
AIAA PAPER 66-760
Report Number: AIAA PAPER 66-760
Accession Number
66A40643
Distribution Limits
Public
Copyright
Other
Keywords
LAMINAR BOUNDARY LAYER
SOLID PROPELLANT ROCKET ENGINE
THERMODYNAMIC PROPERTY
BASE HEATING
EXHAUST GAS
HEAT TRANSFER

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