ANALYTICAL AND EXPERIMENTAL EVALUATION OF THE SUPERSONIC COMBUSTION RAMJET ENGINE. VOLUME 2. COMPONENT EVALUATION

Abstract

This was an experimental and analytical investigation to supply design information for the aerothermo design of a supersonic combustor for a flight test vehicle. The penetration of fuel jets into a supersonic stream was investigated in a cold flow supersonic wind tunnel and combustion test of scale model combustors were conducted in a Hypersonic Arc-Tunnel. Combustion tests of several configurations identified a burner having adequate performance characteristics for achieving the vehicle mission. The aerothermo design of the vehicle combustor was based on this tested configuration. This volume is devoted to investigations of Fuel Injection and Combustion in supersonic airstreams.

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1965
Accession Number
AD0367774

Entities

Organizations

  • General Electric

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Boundary Layer
  • Burning Rate
  • Chemical Reactions
  • Combustion
  • Combustion Products
  • Combustors
  • Computational Fluid Dynamics
  • Data Analysis
  • Heat Transfer
  • Ignition Lag
  • Pressure Distribution
  • Pressure Measurement
  • Supersonic Combustion
  • Supersonic Combustion Ramjet Engines
  • Test And Evaluation
  • Test Facilities
  • Turbulent Mixing

Fields of Study

  • Physics

Readers

  • Fluid Mechanics and Fluid Dynamics.
  • Internal Combustion Engine (ICE) Technology.
  • Systems Analysis and Design

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow