CONVERGENT-DIVERGENT NOZZLE CONTOUR OPTIMIZATION TECHNIQUES,

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)

Document Details

Document Type
Technical Report
Publication Date
Mar 23, 1967
Accession Number
AD0812244

Entities

People

  • John F. Hagewood

Organizations

  • Boeing

Tags

DTIC Thesaurus Topics

  • Axisymmetric
  • Computer Programs
  • Computers
  • Convergent Divergent Nozzles
  • Exhaust Nozzles
  • Geometry
  • Mach Number
  • Mathematics
  • Nozzles
  • Optimization
  • Topology

Fields of Study

  • Physics

Readers

  • Computational Modeling and Simulation
  • Fluid Dynamics.