Static thrust augmentation of a rocket-ejector system with a heated supersonic primary jet /
by Albert J. Simonson and James W. Schmeer.
Description
- Language(s)
-
English
- Published
-
Washington, [D.C.] : National Aeronautics and Space Administration, 1962.
- Summary
-
"An investigation was conducted in order to evaluate the static thrust augmentation attainable through the use of a rocket-ejector system with a heated supersonic primary jet. This system consisted of a cylindrical mixing tube in conjunction with a supersonic nozzle having an expansion ratio of 15 to 1. A hydrogen peroxide gas generator was used to provide heated nozzle flow. An ejector with a bellmouthed inlet provided thrust augmentation up to about 18 percent of the primary rocket thrust, whereas the use of a blunt-lip inlet with elliptical profile provided augmentation up to 9 percent. Axial withdrawal of the rocket nozzle from the ejector provided small gains in thrust augmentation."--P.[1]
- Note
-
Document ID: 19620002195.
"NASA TN D-1261."
"Langley Research Center, Langley Station, Hampton, Va."
"May 1962."
Cover title.
Also available via Internet from NASA Technical Reports Server.
- Physical Description
-
27 p. :
ill. ;
26 cm.
Viewability
Item Link |
Original Source |
Full view
|
University of Illinois at Urbana-Champaign
|