AN INVESTIGATION OF SUPERSONIC COMBUSTION AND HETEROGENEOUS TURBULENT JET MIXING RELATED TO THE DESIGN/OPERATION OF SCRAMJETS.

Abstract

Chemical kinetic calculations of the combustion time in a constant area scramjet combustion (Mo=7) indicate reaction times 0.00001 secs., and show that the combustion process is usually controlled by diffusion. The mixing process in concentric fueld/air jets is investigated by means of integral forms of the equations of motion and slow mixing requires about 50 diameter. Initial contraction of the slow inner jet is predicted by the theory, and verified by experiment. The simulation of scramjet combustion conditions by a shock tunnel is considered feasible. (Author)

Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1965
Accession Number
AD0638665

Entities

People

  • Ian Thomas Osgerby

Organizations

  • University of Sheffield

Tags

Communities of Interest

  • Materials and Manufacturing Processes

DTIC Thesaurus Topics

  • Chemical Reactions
  • Combustion
  • Diameters
  • Diffusion
  • Equations
  • Equations Of Motion
  • Exothermic Reactions
  • Ignition
  • Integrals
  • Reaction Time
  • Shock Tunnels
  • Simulations
  • Supersonic Combustion
  • Supersonic Combustion Ramjet Engines

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Combustion science or combustion engineering.

Technology Areas

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