Hypersonic inlet for a laser powered propulsion system

Harrland, Alan, Doolan, Con, Wheatley, Vincent and Froning, Dave (2011). Hypersonic inlet for a laser powered propulsion system. In: Hans-Albert Eckel and Stefan Scharring, AIP conference proceedings: Beamed Energy Propulsion: Seventh International Symposium. 7th International Symposium on Beamed Energy Propulsion, Ludwigsburg, Germany, (145-157). 10 -14 April 2011. doi:10.1063/1.3657023

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Author Harrland, Alan
Doolan, Con
Wheatley, Vincent
Froning, Dave
Title of paper Hypersonic inlet for a laser powered propulsion system
Conference name 7th International Symposium on Beamed Energy Propulsion
Conference location Ludwigsburg, Germany
Conference dates 10 -14 April 2011
Proceedings title AIP conference proceedings: Beamed Energy Propulsion: Seventh International Symposium   Check publisher's open access policy
Journal name Beamed Energy Propulsion: Seventh International Symposium   Check publisher's open access policy
Place of Publication College Park, MD, United States
Publisher American Institute of Physics
Publication Year 2011
Sub-type Fully published paper
DOI 10.1063/1.3657023
ISBN 9780735409743
ISSN 0094-243X
1551-7616
Editor Hans-Albert Eckel
Stefan Scharring
Volume 1402
Start page 145
End page 157
Total pages 13
Collection year 2012
Language eng
Abstract/Summary Propulsion within the lightcraft concept is produced via laser induced detonation of an incoming hypersonic air stream. This process requires suitable engine configurations that offer good performance over all flight speeds and angles of attack to ensure the required thrust is maintained. Stream traced hypersonic inlets have demonstrated the required performance in conventional hydrocarbon fuelled scramjet engines, and has been applied to the laser powered lightcraft vehicle. This paper will outline the current methodology employed in the inlet design, with a particular focus on the performance of the lightcraft inlet at angles of attack. Fully three-dimensional turbulent computational fluid dynamics simulations have been performed on a variety of inlet configurations. The performance of the lightcraft inlets have been evaluated at differing angles of attack. An idealized laser detonation simulation has also been performed to validate that the lightcraft inlet does not unstart during the laser powered propulsion cycle.
Keyword Hypersonic inlet
Laser induced detonation wave
Stream traced inlet design methodology
Q-Index Code EX
Q-Index Status Confirmed Code
Institutional Status UQ

Document type: Conference Paper
Collections: School of Mechanical & Mining Engineering Publications
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Created: Thu, 13 Oct 2011, 17:00:16 EST by Dr Vincent Wheatley on behalf of School of Mechanical and Mining Engineering