Analysis of Jet Exhausts with Repetitive Shock Structure

Abstract

The report describes an advancement in the state of the art in calculation of the mixing of two concentric (or parallel) streams. The analysis treats the equations of motion governing flow of subsonic or supersonic jets mixing with the surrounding atmosphere. An exhaustive study of full Navier- Stokes solutions and/or simplified mathematical models which retain an elliptic nature did not produce an economically feasible approach to the solution of the jet mixing with shock waves. The approach discussed was selected as an alternative since inclusion of the radial momentum equation and the treatment of lateral pressure gradients is an improvement over current production calculations which may be achieved with nominal computer run times and storage.

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Document Details

Document Type
Technical Report
Publication Date
Sep 01, 1972
Accession Number
AD0750185

Entities

People

  • A. W. Ratliff
  • R. J. Prozan

Organizations

  • Lockheed Martin Missiles and Space

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Boundaries
  • Chemical Reactions
  • Combustion
  • Computational Fluid Dynamics
  • Computational Science
  • Computer Programs
  • Computers
  • Engineering
  • Equations
  • Equations Of Motion
  • Flow
  • Fluid Mechanics
  • Jet Engine Exhaust
  • Jet Engines
  • Pressure Gradients
  • Thermodynamic Properties
  • Turbojet Engines

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Fluid Dynamics.
  • Theoretical Analysis.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flight
  • Hypersonics - Hypersonic Flow