AN EXPERIMENTAL INVESTIGATION OF SHOCK INITIATED DETONATION WAVES IN A FLOWING COMBUSTIBLE MIXTURE

Abstract

The investigation was concerned with the initiation of detonation waves in a subsonically flowing mixture of gaseous hydrogen and oxygen by means of shock waves injected opposite to the direction of the flow. Nominally stoichiometric mixtures at near ambient pressure and stagnation temperature were flowed through a constant area tube at Mach Numbers of approximately .2, .5, and .8. The shock waves were produced by a simple shock tube driver employing helium and mylar diaphragms. Piezoelectric pressure transducers, thin film heat transfer gages, and ionization probes were used to measure the various wave velocities. Results showed that detonation waves can easily be produced in such a flowing mixture. The minimum incident shock wave Mach Number above which detonation always occurred was 2.12 for M(Exit) approx. = .2; 1.75 for M(Exit) approx. = .5; and 1.56 for M(Exit) approx. = .8.

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Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1967
Accession Number
AD0663715

Entities

People

  • Leonard A. Hamilton

Organizations

  • Air Force Institute of Technology

Tags

Communities of Interest

  • Air Platforms
  • Ground and Sea Platforms
  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Boundary Layer
  • Combustion
  • Computer Programs
  • Control Systems
  • Ducts
  • Electrical Equipment
  • Fluid Dynamics
  • Heat Transfer
  • Ignition
  • Measurement
  • Mechanical Engineering
  • Shock Tubes
  • Shock Waves
  • Test Facilities
  • Transducers
  • Waves

Fields of Study

  • Physics

Readers

  • Atmospheric Science / Meteorology, specifically Wind Wave Turbulence.
  • Fluid Dynamics.
  • Plasma Physics.