Ignition and Combustion of Liquid Hydrocarbon Fuels in Supersonic Flow

Abstract

An experimental study was carried out to investigate the combustion of a liquid hydrocarbon (hexane) injected into a supersonic stream. Injection modes included wall and central injection configurations. Extremely rapid and intense heat release phenomena were obtained. It was concluded that this mode of combustion could be made to compete with that of pure gas phase combustion for many technological applications. A preliminary theoretical model of the combustion mechanism was constructed which accounts for many of the observed phenomena, and which explains the very rapid combustion characteristics.

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1969
Accession Number
AD0855766

Entities

People

  • Forman Williams
  • Jose Tamagno
  • Simon Slutsky

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Boundary Layer
  • Burning Rate
  • Chemical Kinetics
  • Chemical Reactions
  • Combustion
  • Flow Fields
  • Fluid Dynamics
  • Fluid Mechanics
  • Geometry
  • Heat Transfer
  • Hydrocarbon Fuels
  • Ignition
  • Ignition Lag
  • Jet Propulsion
  • Mach Number
  • Pressure Distribution

Fields of Study

  • Physics

Readers

  • Fire Suppression Systems Design.
  • Petroleum Engineering
  • Theoretical Analysis.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow