Accession Number:

AD0610179

Title:

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

Descriptive Note:

Master's thesis

Corporate Author:

AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH

Personal Author(s):

• Vaughan, III, John C.

Report Date:

1964-01-01

Pagination or Media Count:

95.0

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.

Descriptors:

• *COMBUSTION CHAMBERS
• *ROCKET ENGINES
• HYDROGEN
• OXYGEN
• COATINGS
• COMBUSTION
• GASEOUS ROCKET PROPELLANTS
• FUEL INJECTORS
• THRUST
• ROCKET NOZZLES
• THERMAL INSULATION
• THESES
• THERMAL PROPERTIES
• PRESSURE

Subject Categories:

• Liquid Propellant Rocket Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE