Accession Number : AD0812244
Title : CONVERGENT-DIVERGENT NOZZLE CONTOUR OPTIMIZATION TECHNIQUES,
Corporate Author : BOEING CO HUNTSVILLE AL LAUNCH SYSTEMS BRANCH
Personal Author(s) : Hagewood, John F.
Report Date : 23 MAR 1967
Pagination or Media Count : 41
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)
Descriptors : (*CONVERGENT DIVERGENT NOZZLES, OPTIMIZATION), NOZZLE THROATS, MATHEMATICAL MODELS, VELOCITY, NOZZLE GAS FLOW, GEOMETRY, PERFORMANCE(ENGINEERING), GEOMETRIC FORMS.
Subject Categories : Fluid Mechanics
Distribution Statement : APPROVED FOR PUBLIC RELEASE