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Optimum thrust-nozzle contours for gas-particle flows.Optimization analysis for axisymmetric rocket motor nozzle design based on assumptions for gas particle flow
Document ID
19670060146
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Hoffman, J. D.
Thompson, H. D.
Date Acquired
August 3, 2013
Publication Date
October 1, 1967
Publication Information
Publication: /AMERICAN INST. OF AERONAUTICS AND ASTRONAUTICS
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 66-538
Report Number: AIAA PAPER 66-538
Accession Number
67A38875
Distribution Limits
Public
Copyright
Other
Keywords
DIFFERENTIAL EQUATION
GAS FLOW
OPTIMIZATION
ROCKET NOZZLE
NOZZLE GEOMETRY

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