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):

Report Date:

1967-06-01

Pagination or Media Count:

110.0

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

Subject Categories:

  • Combustion and Ignition
  • Rocket Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE