Full metadata
Title
Design of Rocket Engine Nozzle Ejectors
Description
This work describes the numerical process developed for use of rocket engine nozzle ejectors. Ejector nozzles, while applied to jet engines extensively, have not been applied to rockets, and have great potential to improve the performance of endoatmospheric rocket propulsion systems. Utilizing the low pressure, high velocity flow in the plume, this secondary structure entrains a secondary mass flow to increase the mass flow of the propulsion system. Rocket engine nozzle ejectors must be designed with the high supersonic conditions associated with rocket engines. These designs rely on the numerical process described in this paper.
Date Created
2014-05
Contributors
- Gibson, Gaines Sullivan (Author)
- Wells, Valana (Thesis director)
- Takahashi, Timothy (Committee member)
- Barrett, The Honors College (Contributor)
- Mechanical and Aerospace Engineering Program (Contributor)
Topical Subject
Resource Type
Extent
20 pages
Language
eng
Copyright Statement
In Copyright
Primary Member of
Series
Academic Year 2013-2014
Handle
https://hdl.handle.net/2286/R.I.22786
Level of coding
minimal
Cataloging Standards
System Created
- 2017-10-30 02:50:57
System Modified
- 2021-08-11 04:09:57
- 3 years 3 months ago
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