CONVERGENT-DIVERGENT NOZZLE CONTOUR OPTIMIZATION TECHNIQUES,

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Abstract:

This document describes in detail a method of analysis to be used in defining the geometric shape of an axisymmetric convergent-divergent exhaust nozzle. This method will define the nozzle wall contour necessary to yield optimum thrust based on the given criterion of exit Mach number. The associated computer program provides the capability for accurately defining the nozzle geometry and predicting the theoretical performance of the nozzle, provided sufficient thermodynamic expansion data are known. Author

Author(s):
Hagewood, John F.
Author Organization(s):
BOEING CO HUNTSVILLE AL LAUNCH SYSTEMS BRANCH
Pagination:
0041

Security Markings

DOCUMENT & CONTEXTUAL SUMMARY

Distribution:
Approved For Public Release

RECORD

Collection: TR
Identifying Numbers
Report Number(s):
D5-13300
 Subject Terms
Communities of Interest:
No COI(s) Identified
Descriptor(s):
(*CONVERGENT DIVERGENT NOZZLES, OPTIMIZATION), NOZZLE THROATS, MATHEMATICAL MODELS, VELOCITY, NOZZLE GAS FLOW, GEOMETRY, PERFORMANCE(ENGINEERING), GEOMETRIC FORMS
Field(s)/Group(s):
Fluid Mechanics
Report Date:
1967 Mar 23