CFD calculations for intake-injection shock-induced-combustion scramjet flight experiments

Mudford, N. R., Mulreany, P. J., McGuire, J. R., Odam, J., Boyce, R. R. and Paull, A. (2003). CFD calculations for intake-injection shock-induced-combustion scramjet flight experiments. In: Proceedings of the AIAA 12th International Space Planes and Hypersonics Systems and Technologies Conference. AIAA 12th International Space Planes and Hypersonics Systems and Technologies Conference, Norfolk, Virginia, (xx-xx). 15-19 December, 2003.


Author Mudford, N. R.
Mulreany, P. J.
McGuire, J. R.
Odam, J.
Boyce, R. R.
Paull, A.
Title of paper CFD calculations for intake-injection shock-induced-combustion scramjet flight experiments
Conference name AIAA 12th International Space Planes and Hypersonics Systems and Technologies Conference
Conference location Norfolk, Virginia
Conference dates 15-19 December, 2003
Proceedings title Proceedings of the AIAA 12th International Space Planes and Hypersonics Systems and Technologies Conference
Journal name 12th AIAA International Space Planes and Hypersonic Systems and Technologies
Place of Publication Reston, Va
Publisher American Institute of Aeronautics and Astronautics
Publication Year 2003
Sub-type Fully published paper
ISBN 9781624100857
Start page xx
End page xx
Total pages 1
Language eng
Formatted Abstract/Summary
Computations are reported of the combusting flows within a hydrogen fuelled model supersonic combustion ramjet (scramjet) operating in a shock tunnel flow. The work is in support of future launches in the HyShot free flight scramjet program. The scramjet simulates all features of a free flight scramjet including inlet compression ramps, combustion chamber and thrust surfaces. The device employs ramp injection and its ignition is thought to be shock induced. The purpose of the investigation is to enhance understanding of the detailed processes which operate within the device. The computational results are compared with pressure measurements for cases of no fuel injection and fuel injection into nitrogen and air coflows. Significant combustion pressure rise has been observed in the latter experiment. The comparison shows that the computations are physically sound and quite accurately predict many features of the flows. However, they fail to predict significant combustion in the fuel + air flow. Detailed examination is made of the computed solution from which it is inferred that the temperatures within the flow are too low for combustion. Therefore, unless the real flows are quite unlike the prediction, combustion would not be expected within them. No convincing explanation for this disparity between experiment and theory has yet been found and investigation is continuing.
Copyright © 2003 by Neil Mudford. Published by the American Institute of Aeronautics and Astronautics, Inc., with permission.
Subjects 090107 Hypersonic Propulsion and Hypersonic Aerodynamics
Q-Index Code E1
Q-Index Status Provisional Code
Institutional Status Unknown
Additional Notes AIAA 2003-7034

 
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Created: Thu, 26 Mar 2009, 00:45:48 EST by Maria Campbell on behalf of School of Engineering