Static thrust augmentation of a rocket-ejector system with a heated supersonic primary jet /
by Albert J. Simonson and James W. Schmeer.

Description

Main Author

Simonson, Albert J.

Related Names

Schmeer, James W.
United States. National Aeronautics and Space Administration.
Langley Research Center.

Language(s)

English

Published

Washington, [D.C.] : National Aeronautics and Space Administration, 1962.

Subjects

Aerodynamics, Supersonic.
Jet engines.
Rocket engines > Rocket engines / Thrust.

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.

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