Accession Number : AD0817968

Title :   INVESTIGATION OF THE THRUST AUGMENTATION CAPABILITY OF A SONIC EJECTOR-AFTERBURNER.

Descriptive Note : Master's thesis,

Corporate Author : AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING

Personal Author(s) : Nidiffer, Kenneth E.

Report Date : JUN 1967

Pagination or Media Count : 110

Abstract : The purpose of this investigation was to determine the thrust augmentation capability of a sonic ejector-afterburner. Two hundred and five tests were conducted at static conditions on a nominal 65 pounds thrust rocket engine using gaseous hydrogen and oxygen as the propellants. Afterburner length and diameter, engine chamber pressure, and propellant mixture ratio were varied to determine the conditions under which optimum performance could be achieved. Performance increased with high chamber pressure, large length to diameter ratios, and high secondary inlet flow areas. (Author)

Descriptors :   (*ROCKET ENGINES, AFTERBURNERS), (*AFTERBURNERS, THRUST AUGMENTATION), OXYGEN, GASEOUS ROCKET PROPELLANTS, INSTRUMENTATION, MIXTURES, COMBUSTION CHAMBERS, NOZZLE THROATS, ROCKET NOZZLES, RAMJET INLETS, JET MIXING FLOW, EXHAUST DIFFUSERS, THESES, SECONDARY FLOW, HYDROGEN, SPECIFIC IMPULSE, REGENERATIVE COOLING, HEAT SINKS, REFRACTORY COATINGS, CADMIUM ALLOYS, EXHAUST NOZZLES, INJECTORS, ORIFICES, STAINLESS STEEL, NOZZLE AREA RATIO.

Subject Categories : Combustion and Ignition
      Rocket Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE