Numerical simulation of the ejector flowfield in a ram rocket engine with multiple rockets.
Contributors: University of Toronto. Institute for Aerospace Studies.
Published: 2004
Language: eng
Number of pages: 76
Subjects: Combustion engineering -- Mathematical models.; Fluid dynamics -- Mathematical models.; Rocket engines.
Description: Analysis shows that evenly distributing the rocket exhaust throughout the entrained air enhances mixing, but does not assure sufficient energy transfer or air entrainment. Examination of the ejector performance from Case-to-Case allows an iterative enhancement process resulting in a performance-balanced ejector.Humanity's access to space is limited to the rocket, restricted by its massive onboard supplies of oxidizer. The ram rocket is a potential alternative. It offers enhanced performance and reduced takeoff weight. Performance is directly related to the amount of air entrained, mixing uniformity of rocket and air flows, and the transfer of energy between them.An ejector configuration by Sislian consisting of two "suspended" annular rockets in an annular ejector is examined. Several Cases are studied by modifying rocket locations and relative sizes. Held constant are the flow parameters and the relative size of total rocket exit area to ejector area. Comparisons are made to Etele and Daines.
Notes: Adviser:  J. P. Sislian.

Thesis (M.A.Sc.)--University of Toronto, 2004.

Electronic version licensed for access by U. of T. users.

Source: Masters Abstracts International, Volume: 43-03, page: 0899.

MICR copy on microfiche (1 microfiche).