STEADY-STATE ROCKET COMBUSTION OF GASEOUS HYDROGEN AND LIQUID OXYGEN. PART 2: ANALYSIS FOR COAXIAL JET INJECTION

Abstract

Simultaneous equations describing rocket propellant injection, atomization, mixing, vaporization, and combustion are formulated for a cylindrical liquid oxygen jet surrounded by an annular gaseous hydrogen stream. The formulation is based on division of the combustion chamber into a nonburning region near the injector and a combustion region further downstream. Processes in the nonburning region are required to satisfy certain combustibility criteria before combustion is possible. The propellants then pass through a plane flame front into the combustion region. A simplified treatment of turbulent mixing between unlike reacting gas streams, one of which contains a liquid oxygen spray, characterizes the combustion region model. Solutions of the system of equations, obtained with a digital computer program, are detailed, discussed, and compared favorably with experimental information from Part I.

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1965
Accession Number
AD0623401

Entities

People

  • L. P. Combs
  • M. D. Schuman

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Boundary Layer
  • Combustion
  • Combustion Chambers
  • Combustion Products
  • Combustors
  • Digital Computers
  • Equations
  • Flames
  • Flammability
  • Geometry
  • Heat Transfer
  • Ignition
  • Liquid Oxygen
  • Rocket Engines
  • Transport Properties
  • Turbulent Mixing

Fields of Study

  • Physics

Readers

  • Combustion science or combustion engineering.
  • Fluid Dynamics.
  • Rocket Propulsion.