Experimental Investigation of Combustion Stabilization in Supersonic Flow Using Free Recirculation Zones

Abstract

Final report summarizes shortly main results of the quarterly reports and presents experimental results on self-ignition and combustion stabilization in supersonic flow using free recirculation zone. Tests are conducted at hypersonic facility TsAGI T-131B. Measurements are performed in a nearly matched supersonic jet at the exit of two-dimensional channel over Mach number range M=2.O-2.8 at stagnation temperature range Tt=1200-1400K. initial thickness of jet was equal 67 mm. Self-ignition and stabilization are obtained at Tt=1400K. Self-ignition was absent at Tt=1200K, 1300K. Thickness of free recirculation zone was about 25-30 mm.

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Document Details

Document Type
Technical Report
Publication Date
Aug 01, 1997
Accession Number
ADA336192

Tags

Communities of Interest

  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Boundary Layer
  • Combustion
  • Contracts
  • Flow Visualization
  • Fluid Dynamics
  • Fluid Mechanics
  • Ignition
  • Mach Number
  • Photography
  • Pressure Distribution
  • Pressure Measurement
  • Stagnation Pressure
  • Static Pressure
  • Test Facilities
  • Two Dimensional
  • Vortex Generators
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Combustion science or combustion engineering.
  • Fluid Dynamics.
  • Internal Combustion Engine (ICE) Technology.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow