The domain of the scramjet

Abstract

Restricted accessMoreSectionsView PDF ToolsAdd to favoritesDownload CitationsTrack Citations ShareShare onFacebookTwitterLinked InRedditEmail Cite this article Townend Leo H. 1999The domain of the scramjetPhil. Trans. R. Soc. A.3572317–2334http://doi.org/10.1098/rsta.1999.0433SectionRestricted accessThe domain of the scramjet Leo H. Townend Leo H. Townend Advanced Propulsion and Energy Control Systems Ltd, 3 Hawkley Hurst, Hawkley, Hants GU33 6NS, UK Google Scholar Find this author on PubMed Search for more papers by this author Leo H. Townend Leo H. Townend Advanced Propulsion and Energy Control Systems Ltd, 3 Hawkley Hurst, Hawkley, Hants GU33 6NS, UK Google Scholar Find this author on PubMed Search for more papers by this author Published:01 August 1999https://doi.org/10.1098/rsta.1999.0433AbstractAs flight speed increases into the hypersonic regime, the stagnation pressure and temperature inside the engine become so great that, for practical structures of acceptable mass, the flow must pass through the engine at supersonic, rather than subsonic, speeds, hence the term ‘scramjet’ (supersonic combustion ramjet). The classic application for the scramjet is to the long–range airliner offering extended hypersonic flight. It is also widely accepted as a possible complement to the rockets conventionally used for space launchers. This paper explores the topic of how scramjets may best be used and is the first Frederick S. Billig Lecture in Hypersonics of the International Society for Air Breathing Engines, to be given at the 14th ISABE Symposium, 5 to 12 September 1999 in Florence, Italy. Previous ArticleNext Article VIEW FULL TEXT DOWNLOAD PDF FiguresRelatedReferencesDetailsCited by Gildfind D, Morgan R, McGilvray M and Jacobs P (2012) Simulation of High Mach Number Scramjet Flow Conditions using the X2 Expansion Tube 18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference, 10.2514/6.2012-5954, 978-1-60086-931-0, Online publication date: 24-Sep-2012. Yankui W, Shuifeng Y, Dongjun Z and Xueying D (2007) Design of Waverider Configuration with High Lift-Drag Ratio, Journal of Aircraft, 10.2514/1.22669, 44:1, (144-148), Online publication date: 1-Jan-2007. Silvester T, McIntyre T and Morgan R (2007) Superorbital expansion tube tests of a caret waverider, Shock Waves, 10.1007/s00193-007-0100-3, 17:1-2, (51-63), Online publication date: 1-Aug-2007. Curran E (2001) Scramjet Engines: The First Forty Years, Journal of Propulsion and Power, 10.2514/2.5875, 17:6, (1138-1148), Online publication date: 1-Nov-2001. (2001) Table of Contents Scramjet Propulsion, 10.2514/5.9781600866609.0000.0000, (i-xxvii), Online publication date: 1-Jan-2001. This Issue01 August 1999Volume 357Issue 1759Theme Issue ‘Hypersonic aircraft: lifting re–entry and launch’ compiled by L. H. Townend Article InformationDOI:https://doi.org/10.1098/rsta.1999.0433Published by:Royal SocietyPrint ISSN:1364-503XOnline ISSN:1471-2962History: Published online01/08/1999Published in print01/08/1999 License: Citations and impact Keywordskerosene fuelsmall SSTO aerospaceplanescooled compression processexternal combustionscramjet second stagesscramjet