EFFECT OF CHAMBER PRESSURE ON THE PERFORMANCE OF A SMALL REVERSE-FLOW ROCKET ENGINE

Abstract

Experimental tests were made on a small reverse-flow rocket engine utilizing gaseous hydrogen and oxygen as propellants. The engine was operated at chamber pressures from 50 to 150 psia and developed thrusts from 40 to 150 pounds. The majority of tests were conducted at chamber pressures of 60 and 100 psia. Results indicated that the same maximum characteristic exhaust velocity (7960 fps) and combustion efficiency (97%) were obtained for both these chamber pressures. However, with increasing chamber pressure the optimum mixture ratio increased. In addition, it was found that the best combustion chamber shape was spherical.

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Document Details

Document Type
Technical Report
Publication Date
Jan 01, 1964
Accession Number
AD0610179

Entities

People

  • John C. Vaughan Iii

Organizations

  • Air Force Institute of Technology

Tags

Communities of Interest

  • Ground and Sea Platforms
  • Human Systems
  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Combustion
  • Combustion Chambers
  • Computer Programs
  • Crystal Structure
  • Fluid Dynamics
  • Fluid Mechanics
  • Heat Transfer
  • Measurement
  • Mechanics
  • New York
  • Pressure Gages
  • Propellants
  • Rocket Engines
  • Tensile Strength
  • Test Facilities
  • Thermal Conductivity

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.