SUPERSONIC HYDROGEN COMBUSTION STUDIES

Abstract

The purpose of this test was to develop diagnostic techniques for the detection of hydrogen combustion in a hypersonic high temperature air stream. This was accomplished by ejecting hydrogen through sonic nozzles oriented normal to the airstream in the case of the flat plate model and at a 45-degree angle downstream in the case of the stepped flat plate model. The hydrogen gas was ejected into a high temperature airstream (T sub 0 4000 R) at Mach Number 4.14 to 4.24. The data is presented in three forms: (1) photographs; (2) graphical; and (3) oscillo graph traces.

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Document Details

Document Type
Technical Report
Publication Date
Apr 01, 1963
Accession Number
AD0408988

Entities

People

  • Duane R. Burnett
  • Paul Czysz

Tags

Communities of Interest

  • Space

DTIC Thesaurus Topics

  • Air Force
  • Air Force Facilities
  • Boundary Layer
  • Cameras
  • Combustion
  • Computational Fluid Dynamics
  • Engineering
  • Flat Plate Models
  • High Temperature
  • Mach Number
  • Oscillographs
  • Photographic Equipment
  • Photographic Materials
  • Photographs
  • Photography
  • Pressure Distribution
  • Test Facilities

Fields of Study

  • Physics

Readers

  • Explosive Engineering.
  • Fluid Dynamics.
  • Plasma Physics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow