A Numerical Routine for Defining Rocket Exhaust Characteristics and Impingement Effects

Abstract

This report presents a computer method for predicting the thermodynamic properties of decaying rocket exhaust plumes. A momentum integral technique is the chosen method for the program. This method describes accurately the plume parameters of pitot pressure, total temperature, and velocity at discrete axial and radial locations. Included in the report are (1) The development of the analytical method (2) An empirical determination of the mixing parameter K (3) The computer code that was developed (4) Typical results as compared to a similar method and actual measured data. Program listings are provided with a description of their use. Also included is a plot program for graphically presenting constant contour lines of pressure, temperature, and velocity within the plume flow field.

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Document Details

Document Type
Technical Report
Publication Date
Sep 01, 1988
Accession Number
ADA206323

Entities

People

  • Roswell W. Nourse

Organizations

  • United States Army Aviation and Missile Command

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Computer Programs
  • Computers
  • Exhaust Gases
  • Exhaust Plumes
  • Gases
  • Integrals
  • Mach Number
  • Molecular Weight
  • Momentum
  • Payload
  • Physical Properties
  • Plastic Explosives
  • Plumes
  • Rocket Engines
  • Rocket Exhaust
  • Thermodynamic Properties
  • Two Dimensional

Readers

  • Approximation Theory.
  • Computer Science.
  • Rocket Propulsion.