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Results from short-duration altitude-chamber techniques for simulating rocket 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
19670048114
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Wilson, H. B., Jr.
Date Acquired
August 3, 2013
Publication Date
May 1, 1967
Publication Information
Publication: /AMERICAN INST. OF AERONAUTICS AND ASTRONAUTICS
Subject Category
Facilities, Research, And Support
Report/Patent Number
AIAA PAPER 66-760
Report Number: AIAA PAPER 66-760
Accession Number
67A26843
Distribution Limits
Public
Copyright
Other
Keywords
SOLID PROPELLANT ROCKET ENGINE
LAMINAR BOUNDARY LAYER
BASE HEATING
EXHAUST GAS
THERMODYNAMIC PROPERTY
HEAT TRANSFER

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