Accession Number : AD0832454
Title : AN INVESTIGATION OF THE EFFECTS OF SECONDARY STREAM TURBULATION ON THE THRUST AUGMENTATION OF AN EJECTOR-AFTERBURNER.
Descriptive Note : Master's thesis,
Corporate Author : AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING
Personal Author(s) : Adam, Wallace B.
Report Date : MAR 1968
Pagination or Media Count : 100
Abstract : Secondary stream turbulation of a supersonic ejector-afterburner was investigated using a nominal 65 pounds thrust gaseous hydrogen-oxygen rocket engine. The afterburner had a length-to-diameter ratio of 9 and an afterburner exit to nozzle-exit area ratio of 5.1. Several turbulator configurations, with aerodynamic blockage ratios from 0.123 to 0.516, were tested at three locations relative to the secondary stream inlet. Results showed that at mixture ratios less than 0.8, the performance of the ejector-afterburner could be improved with secondary stream turbulation. (Author)
Descriptors : *THRUST AUGMENTATION), (*LIQUID PROPELLANT ROCKET ENGINES, AFTERBURNERS), (*AFTERBURNERS, SECONDARY FLOW, TURBULENCE, SPECIFIC IMPULSE, JET MIXING FLOW, ROCKET NOZZLES, SUPERSONIC CHARACTERISTICS, PERFORMANCE(ENGINEERING), HYDROGEN, OXYGEN, THESES.
Subject Categories : Fluid Mechanics
Jet and Gas Turbine Engines
Liquid Propellant Rocket Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE