Studies of turbojet engines for hypersonic propulsion.

This thesis contains the results of a theoretical analysis of the performance of an inverted turbojet cycle as a thrust power unit. This system is compared with a conventional turbojet with and without reheat and pre-cooling. Within the limitations of the analysis it is seen that the domain of air b...

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Bibliographic Details
Main Author:	Sreenath, Ananthapur. V.
Other Authors:	Mordell, D. (Supervisor)
Format:	Others
Language:	en
Published:	McGill University 1961
Subjects:	Mechanical Engineering.
Online Access:	http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=113538

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spelling	ndltd-LACETR-oai-collectionscanada.gc.ca-QMM.1135382014-02-13T04:09:44ZStudies of turbojet engines for hypersonic propulsion.Sreenath, Ananthapur. V.Mechanical Engineering.This thesis contains the results of a theoretical analysis of the performance of an inverted turbojet cycle as a thrust power unit. This system is compared with a conventional turbojet with and without reheat and pre-cooling. Within the limitations of the analysis it is seen that the domain of air breathing engines for propulsion can be extended to hypersonic vehicles. The inverted turbojet is an economical cruising engine for hypersonic vehicles at Mach numbers 5-6. However a conventional turbojet with pre-cooling and reheat can power a vehicle throughout the range of Mach 0 to Mach 6.McGill UniversityMordell, D. (Supervisor)1961Electronic Thesis or Dissertationapplication/pdfenalephsysno: NNNNNNNNNTheses scanned by McGill Library.All items in eScholarship@McGill are protected by copyright with all rights reserved unless otherwise indicated.Master of Engineering. (Department of Engineering.) http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=113538
collection	NDLTD
language	en
format	Others
sources	NDLTD
topic	Mechanical Engineering.
spellingShingle	Mechanical Engineering. Sreenath, Ananthapur. V. Studies of turbojet engines for hypersonic propulsion.
description	This thesis contains the results of a theoretical analysis of the performance of an inverted turbojet cycle as a thrust power unit. This system is compared with a conventional turbojet with and without reheat and pre-cooling. Within the limitations of the analysis it is seen that the domain of air breathing engines for propulsion can be extended to hypersonic vehicles. The inverted turbojet is an economical cruising engine for hypersonic vehicles at Mach numbers 5-6. However a conventional turbojet with pre-cooling and reheat can power a vehicle throughout the range of Mach 0 to Mach 6.
author2	Mordell, D. (Supervisor)
author_facet	Mordell, D. (Supervisor) Sreenath, Ananthapur. V.
author	Sreenath, Ananthapur. V.
author_sort	Sreenath, Ananthapur. V.
title	Studies of turbojet engines for hypersonic propulsion.
title_short	Studies of turbojet engines for hypersonic propulsion.
title_full	Studies of turbojet engines for hypersonic propulsion.
title_fullStr	Studies of turbojet engines for hypersonic propulsion.
title_full_unstemmed	Studies of turbojet engines for hypersonic propulsion.
title_sort	studies of turbojet engines for hypersonic propulsion.
publisher	McGill University
publishDate	1961
url	http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=113538
work_keys_str_mv	AT sreenathananthapurv studiesofturbojetenginesforhypersonicpropulsion
_version_	1716646429799219200

Studies of turbojet engines for hypersonic propulsion.

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