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A general method for determining optimum thrust nozzle contours for chemically reacting gas flows.Optimum thrust nozzle contours for chemically reacting gas flows, obtaining set of partial differential equations for gas dynamic properties
Document ID
19670044389
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Hoffman, J. D.
Date Acquired
August 3, 2013
Publication Date
April 1, 1967
Publication Information
Publication: /AMERICAN INST. OF AERONAUTICS AND ASTRONAUTICS
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 66-638
Report Number: AIAA PAPER 66-638
Accession Number
67A23118
Funding Number(s)
CONTRACT_GRANT: NSG-592
Distribution Limits
Public
Copyright
Other
Keywords
SUPERSONIC NOZZLE
NOZZLE GEOMETRY
PARTIAL DIFFERENTIAL EQUATION
OPTIMUM THRUST PROGRAMMING
GAS DYNAMICS

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