High temperature gas effects for converging conical shocks

Zander, F., Molder, S., Morgan, R. G., Jacobs, P. A. and Gollan, R. J. (2012). High temperature gas effects for converging conical shocks. In: 18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference 2012. 18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference 2012, Tours, France, (). 24 - 28 September 2012. doi:10.2514/6.2012-5939


Author Zander, F.
Molder, S.
Morgan, R. G.
Jacobs, P. A.
Gollan, R. J.
Title of paper High temperature gas effects for converging conical shocks
Conference name 18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference 2012
Conference location Tours, France
Conference dates 24 - 28 September 2012
Proceedings title 18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference 2012
Place of Publication Red Hook, N.Y
Publisher Currans
Publication Year 2012
Year available 2012
Sub-type Fully published paper
DOI 10.2514/6.2012-5939
ISBN 9781600869310
9781627481823
1627481826
Total pages 7
Collection year 2013
Language eng
Abstract/Summary The flow associated with internal, conical shocks provides a useful basis for the design of supersonic and hypersonic air intakes. The analytical solutions to these flows, however, are limited to ideal gas models, but as the flow speeds increase into the hypervelocity regime, the high temperature gas effects may invalidate this ideal analysis. Chemical and thermal changes cause distortion to shock shape, which significantly alters the flow field and changes the behaviour of the shock reflections on the axis of symmetry. The computational work conducted here shows that high temperature effects can prevent the occurrence of Mach reflection for a given shock angle and hence drastically change the flow field. The computational results also show the formation of a strong curved shock structure at the centreline which requires further investigation. A preliminary experimental campaign was conducted in the X2 expansion tube at Mach 8.1 and Mach 10 flows. Experimental imagery of the shock structure formation at the centre line clearly exhibited the upstream travelling, bulbous Mach stem that had been predicted by CFD analysis.
Subjects 1912 Space and Planetary Science
2202 History and Philosophy of Specific Fields
2207 Control and Systems Engineering
Q-Index Code E1
Q-Index Status Provisional Code
Institutional Status UQ

Document type: Conference Paper
Collections: School of Mechanical & Mining Engineering Publications
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Created: Wed, 27 Nov 2013, 15:54:24 EST by Deanna Mahony on behalf of School of Mechanical and Mining Engineering