THE FAR FIELD OF A ROCKET EXHAUST JET AT LOW AND MODERATE ALTITUDES

Abstract

A method is given for predicting the flow field of a rocket exhaust plume at distances far removed from the nozzle exit at altitudes where afterburning of the exhaust is appreciable. The calculation combines a fluid mechanical analysis of turbulent mixing due to Libby with the adiabatic flame temperature calculation of Boynton and Neu. The eddy viscosity is determined from a consideration of conditions under which compressible turbulent flows appear to exhibit self-preserving behavior. Instructions are given for preparing input to two computer programs which are based on the analysis in the report. In two appendices, it is shown how the eddy viscosity constants may be derived from incompressible jet flow data and a comparison of the results of the present calculation with experimental wind-tunnel rocket exhaust behavior is given.

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1964
Accession Number
AD0612018

Entities

People

  • Frederick P. Boynton

Organizations

  • General Dynamics

Tags

Communities of Interest

  • Air Platforms
  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Altitude
  • Boundary Layer
  • Chemical Reactions
  • Combustion
  • Computer Programs
  • Computers
  • Exhaust Gases
  • Exhaust Plumes
  • Flow
  • Flow Fields
  • Fluids
  • Jet Flow
  • Rocket Exhaust
  • Turbulent Flow
  • Turbulent Mixing
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Fluid Mechanics and Fluid Dynamics.