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Accession Number:
AD0832454
Title:
AN INVESTIGATION OF THE EFFECTS OF SECONDARY STREAM TURBULATION ON THE THRUST AUGMENTATION OF AN EJECTOR-AFTERBURNER.
Corporate Author:
AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING
Report Date:
1968-03-01
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
Descriptive Note:
Master's thesis,
Pages:
0100
File Size:
0.00MB
