SUPERSONIC AXISYMMETRIC NOZZLE DESIGN BY MASS FLOW TECHNIQUES UTILIZING A DIGITAL COMPUTER

Abstract

This report presents a method to design the inviscid wall contour of a supersonic, axisymmetric nozzle producing uniform parallel flow at the exit. The calculation methods used are restricted to a perfect gas. The axis velocity distribution must be specified. A complete flow pattern within the nozzle is computed by the method of characteristics beginning at Mach 1.0 on the axis and extending to the region of uniform parallel flow at the exit. The wall points are calculated by means of a mass integration technique. The methods of calculation included have been programmed in Fortran II language, and a complete listing of the program is given.

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1964
Accession Number
AD0601589

Entities

People

  • D. B. Ramsay
  • W. C. Moger

Organizations

  • Arnold Engineering Development Complex

Tags

DTIC Thesaurus Topics

  • Axisymmetric
  • Computer Programs
  • Computers
  • Differential Equations
  • Digital Computers
  • Equations
  • Flow
  • Government Procurement
  • Governments
  • Intellectual Property
  • Language
  • Mach Number
  • Mass Flow
  • Method Of Characteristics
  • Nomenclature
  • Partial Differential Equations
  • Procedures (Computers)

Fields of Study

  • Physics

Readers

  • Business Analytics
  • Combustion and Flow Dynamics.
  • Parallel and Distributed Computing.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow