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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
19660057309
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Hoffman, J. D.
Date Acquired
August 3, 2013
Publication Date
June 1, 1966
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 66-638
Report Number: AIAA PAPER 66-638
Accession Number
66A36599
Funding Number(s)
CONTRACT_GRANT: NSG-598
Distribution Limits
Public
Copyright
Other
Keywords
GAS DYNAMICS
NOZZLE GEOMETRY
PARTIAL DIFFERENTIAL EQUATION
SUPERSONIC NOZZLE
OPTIMUM THRUST PROGRAMMING

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