Analysis and Computer Program for Evaluation of Airbreathing Propulsion Exhaust Nozzle Performance

Abstract

An analytical technique based on the time-dependent flow equations has been developed to predict the inviscid transonic flow field in axisymmetric propulsion nozzles. The analysis includes the treatment of axisymmetric nonuniform nozzle inlet profiles of total pressure, total temperature, specific heat, and molecular weight. The analysis is also capable of considering convergent-divergent, convergent, and shrouded or unshrouded plug nozzle geometries. A computer listing and three sample calculations are presented to illustrate some of the capabilities of the program.

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Document Details

Document Type
Technical Report
Publication Date
May 01, 1973
Accession Number
AD0760541

Entities

People

  • S. Wehofer
  • W. C. Moger

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Air Platforms
  • C4I
  • Energy and Power Technologies
  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Boundaries
  • Computer Programming
  • Computer Programs
  • Computers
  • Engineering
  • Equations
  • Flow
  • Flow Fields
  • Gas Turbine Nozzles
  • Geometry
  • Mach Number
  • Nozzles
  • Plug Nozzles
  • Pressure Distribution
  • Specific Heat
  • Turbines

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Computer Science.
  • Finite Element Method (FEM) for solving Partial Differential Equations (PDEs)