Comparison of Computation and Measurements in a Supersonic Cavity Combustor

Sacco, Alessandro, O'Byrne, Sean, Neely, Andrew J., Boyce, Russell R. and Mudford, Neil R. (2006). Comparison of Computation and Measurements in a Supersonic Cavity Combustor. In: 14th AIAA/AHI International Space Planes and Hypersonic Systems and Technologies Conference - A Collection of Technical Papers. 14th AIAA/AHI Space Planes and Hypersonic Systems and Technologies Conference, National Convention Centre, Canberra, ACT, (148-158). 6-9 November, 2006.


Author Sacco, Alessandro
O'Byrne, Sean
Neely, Andrew J.
Boyce, Russell R.
Mudford, Neil R.
Title of paper Comparison of Computation and Measurements in a Supersonic Cavity Combustor
Conference name 14th AIAA/AHI Space Planes and Hypersonic Systems and Technologies Conference
Conference location National Convention Centre, Canberra, ACT
Conference dates 6-9 November, 2006
Proceedings title 14th AIAA/AHI International Space Planes and Hypersonic Systems and Technologies Conference - A Collection of Technical Papers
Journal name A Collection of Technical Papers - 14th AIAA/AHI International Space Planes and Hypersonic Systems and Technologies Conference
Place of Publication Reston, Virginia
Publisher American Institute of Aeronautics and Astronautics
Publication Year 2006
Sub-type Fully published paper
ISBN 1563478269
9781563478260
Volume 1
Start page 148
End page 158
Total pages 11
Language eng
Abstract/Summary Computations are presented for supersonic combustion in a cavity combustor at a °ight Mach number of 11.4 and an altitude of 29 km. The e®ects of reaction mechanism choice and the presence of radical species in the facility nozzle °ow on the computations are presented, showing that including nitric oxide reactions in the reaction mechanism increases the peak temperature and pressure in the °ow¯eld, but increases the ignition delay time. The computations are compared to °oor static pressure measurements and to planar laserinduced °uorescence visualisations of the hydroxyl radical. Generally good agreement is achieved with the location of the hydroxyl radical in the combustor, but the static pressure is over-predicted by between 15 and 20 percent
Subjects 090107 Hypersonic Propulsion and Hypersonic Aerodynamics
Q-Index Code E1
Institutional Status Non-UQ
Additional Notes AIAA 2006-7916

 
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Created: Thu, 26 Mar 2009, 10:45:14 EST by Maria Campbell on behalf of School of Engineering