Effects of Upstream Injection on Scramjet Performance Using an Entropy-Based Method

McGilvray, M and Morgan, RG (2009) Effects of Upstream Injection on Scramjet Performance Using an Entropy-Based Method. JOURNAL OF PROPULSION AND POWER, 25 2: 295-302. doi:10.2514/1.38325


Author McGilvray, M
Morgan, RG
Title Effects of Upstream Injection on Scramjet Performance Using an Entropy-Based Method
Journal name JOURNAL OF PROPULSION AND POWER   Check publisher's open access policy
ISSN 0748-4658
Publication date 2009-03-01
Year available 2009
Sub-type Article (original research)
DOI 10.2514/1.38325
Open Access Status Not Open Access
Volume 25
Issue 2
Start page 295
End page 302
Total pages 7
Editor Vigor Yang
Becky Rivard
Place of publication United States
Publisher American Institute of Aeronautics and Astronautics, Inc.
Language eng
Subject C1
880399 Aerospace Transport not elsewhere classified
090107 Hypersonic Propulsion and Hypersonic Aerodynamics
Abstract Upstream injection has the potential for increasing the overall performance of a scramjet by reducing the overall length required to complete combustion and, thereby, reducing overall vehicle frictional drug. However, high flow losses will be incurred by injecting a fuel on the inlet where the Mach number is high. A simple overall approach based on entropy generation was used to investigate the effect or flow losses oil overall performance. This showed that the injection flow losses can he quite high for upstream injection when compared with conventional combustor injection. An inviseid analysis of a two-dimensional scramjet at a Mach 10 flight condition found that a significant loss In overall performance of the engine occurs if the bulk of injection is undertaken on the intake. Estimates of viscous effects in a scramjet combustor showed that depending on the reduction of the mixing length achieved in the combustor, the upstream injection flow losses could he substantially recovered, making it an advantageous design option. The analysis technique developed, like similar simple analysis methodologies, provides a useful understanding of the physical processes that influence thrust production and can also be used to quickly evaluate and optimize potential configurations before starting detailed flow-field simulations.
Keyword HYPERSONIC ENGINES
THRUST LOSSES
Combustion
design
Q-Index Code C1
Q-Index Status Confirmed Code

Document type: Journal Article
Sub-type: Article (original research)
Collections: 2010 Higher Education Research Data Collection
School of Mechanical & Mining Engineering Publications
 
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Created: Thu, 03 Sep 2009, 18:27:01 EST by Mr Andrew Martlew on behalf of School of Mechanical and Mining Engineering