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A general method for determining 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
19660057308
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Hoffman, J. D.
Thompson, H. D.
Date Acquired
August 3, 2013
Publication Date
June 1, 1966
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 66-538
Report Number: AIAA PAPER 66-538
Accession Number
66A36598
Distribution Limits
Public
Copyright
Other
Keywords
GAS FLOW
ROCKET NOZZLE
DIFFERENTIAL EQUATION
NOZZLE GEOMETRY
OPTIMIZATION

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