AN APPROXIMATE METHOD FOR CALCULATING THE FLOW FIELD OF A ROCKET EXHAUSTING INTO A VACUUM

Abstract

An approximate method for determining the far field flow properties of a rocket exhausting into a vacuum is presented. The technique described is based on radial flow and assumes a density variation both along and normal to the jet centerline. The resulting jet flow field is compared with solutions by the method of characteristics and is shown to have good agreement. Example calculations are provided to demonstrate the present method.

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Document Details

Document Type
Technical Report
Publication Date
Jun 15, 1964
Accession Number
AD0601616

Entities

People

  • A. I. Karydas
  • H. T. Kato

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Conical Nozzles
  • Exhaust Gases
  • Far Field
  • Flow
  • Flow Fields
  • Fluid Dynamics
  • Fluid Mechanics
  • Gases
  • Geometry
  • Jet Flow
  • Mach Number
  • Method Of Characteristics
  • Radial Flow
  • Rocket Exhaust
  • Space Systems
  • Specific Heat

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.
  • Fluid Mechanics and Fluid Dynamics.
  • Regression Analysis.