A theoretical performance investigation of an afterburning turbofan engine
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Authors
Bell, James Franklin
Subjects
Advisors
Vavra, M. N.
Date of Issue
1962
Date
1962
Publisher
Monterey, California: U.S. Naval Postgraduate School
Language
en_US
Abstract
This study presents results of a theoretical evaluation of the performance of an afterburning turbofan engine when used for high altitude, high speed flight. The calculated performance is compared with that of a conventional turbojet, and also a combination ram- turbojet, by means of the performance parameters of specific fuel consumption and specific thrust. As the study involved a considerable
amount of calculations, the problem was coded in Fortran computer language by the writer. The results of the study were generated by the Control Data Corporation model 1604 digital computer of the Postgraduate School. The results of the study indicate that above
Mach 2 the afterburning turbofan shows an increasing performance advantage with increasing Mach number and altitude over the turbojet engine.
The work was conducted at the U. S. Naval Postgraduate School, Monterey, California.
This study present results of a theoretical evaluation of the performance of an afterburning turbofan engine when used for high altitude, high speed flight. The calculated performance is compared with that of a conventional turbojet, and also a combination ram-turbojet, by means of the performance parameters of specific fuel consumption and specific thrust. As the study involved a considerable amount of calculations, the problem was coded in FORTRAN computer language by the writer. The results of the study were generated by the Control Data Corporation model 1604 digital computer of the Postgraduate School. The results of the study indicates that above Mach 2 the after burning turbofan shows an increasing performance advantage with increasing Mach number and altitude over the turbojet engine. The work was conducted at the U.S. Naval Postgraduate School, Monterey, California.
This study present results of a theoretical evaluation of the performance of an afterburning turbofan engine when used for high altitude, high speed flight. The calculated performance is compared with that of a conventional turbojet, and also a combination ram-turbojet, by means of the performance parameters of specific fuel consumption and specific thrust. As the study involved a considerable amount of calculations, the problem was coded in FORTRAN computer language by the writer. The results of the study were generated by the Control Data Corporation model 1604 digital computer of the Postgraduate School. The results of the study indicates that above Mach 2 the after burning turbofan shows an increasing performance advantage with increasing Mach number and altitude over the turbojet engine. The work was conducted at the U.S. Naval Postgraduate School, Monterey, California.
Type
Thesis
Description
URI
Series/Report No
Department
Department of Aeronautics
Organization
Naval Postgraduate School (U.S.)