Boundary layer combustion for viscous drag reduction in practical scramjet configurations

Chan, W. Y. K., Mee, D. J., Smart, M. K., Turner, J. C. and Stalker, R. J. (2010). Boundary layer combustion for viscous drag reduction in practical scramjet configurations. In: I. Grant 27th International Congress of The Aeronautical Sciences (ICAS 2010), Nice, France, (1-10). 19-24 September 2010.

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Name Description MIMEType Size Downloads
Author Chan, W. Y. K.
Mee, D. J.
Smart, M. K.
Turner, J. C.
Stalker, R. J.
Title of paper Boundary layer combustion for viscous drag reduction in practical scramjet configurations
Conference Paper Type Fully Published Paper
Conference name 27th International Congress of The Aeronautical Sciences (ICAS 2010)    (ERA 2010 Rank B)
Conference location Nice, France
Conference dates 19-24 September 2010
Editor I. Grant
Place published United Kingdom
Publisher Optimage
Publication date 2010
ISBN 9780956533302
Start page 1
End page 10
Total pages 10
Collection year 2011
Language eng
Abstract/Summary A key issue that can affect the implementation of boundary layer combustion for viscous drag reduction in scramjet combustors is the potential of non-uniform flow entering the combustor from the inlet. Experiments were conducted in the T4 Stalker tube to study the effects of these flow nonuniformities on boundary layer combustion in a circular constant-area combustor. A Rectangularto- Elliptical-Shape-Transition (REST) inlet, typical of the type of inlets proposed for self-starting scramjet inlets, was attached upstream of the combustor in the current experiments. A numerical simulation of the flow through the REST inlet showed that the inlet generated a non-uniform outflow that had shock and expansion waves. The skin friction drag measured on the inner surface of the combustor indicated a reduction in skin friction drag of 30% when hydrogen burns in the boundary layer. More importantly, these experiments showed that a significant level of skin friction reduction due to boundary layer combustion was still achievable even in the presence of flow non-uniformities from the REST inlet.
Keyword Boundary layer combustion
Turbulent skin friction drag
Drag reduction
Flow non-uniformity
Q-Index Code E1
Q-Index Status Confirmed Code
Institutional Status UQ

Document type: Conference Paper
Sub-type: Fully Published Paper
Collections: School of Mechanical & Mining Engineering Publications
Official 2011 Collection
ERA 2012 Admin Only
 
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Created: Fri, 04 Feb 2011, 23:40:55 EST by Mr Wilson Chan on behalf of School of Mechanical and Mining Engineering