Flow Studies on a Hydrogen-Fueled Cavity Flame-Holder Scramjet

Neely, Andrew J., Stotz, Ingo, O’Byrne, Sean, Boyce, Russell R., Mudford, Neil R. and Houwing, A. F. P. (2005). Flow Studies on a Hydrogen-Fueled Cavity Flame-Holder Scramjet. In: Proceedings of the AIAA/CIRA 13th International Space Planes and Hypersonics Systems and Technologies Conference. AIAA/CIRA 13th International Space Planes and Hypersonics Systems and Technologies Conference, Capua, Italy, (1478-1485). 16-20 May 2005.


Author Neely, Andrew J.
Stotz, Ingo
O’Byrne, Sean
Boyce, Russell R.
Mudford, Neil R.
Houwing, A. F. P.
Title of paper Flow Studies on a Hydrogen-Fueled Cavity Flame-Holder Scramjet
Conference name AIAA/CIRA 13th International Space Planes and Hypersonics Systems and Technologies Conference
Conference location Capua, Italy
Conference dates 16-20 May 2005
Convener American Institute of Aeronautics and Astronautics
Proceedings title Proceedings of the AIAA/CIRA 13th International Space Planes and Hypersonics Systems and Technologies Conference
Journal name A Collection of Technical Papers - 13th AIAA/CIRA International Space Planes and Hypersonic Systems and Technologies Conference
Place of Publication Reston, VA
Publisher American Institute of Aeronautics and Astronautics
Publication Year 2005
Sub-type Fully published paper
ISBN 1563477297
9781563477294
Volume 3
Start page 1478
End page 1485
Total pages 8
Language eng
Abstract/Summary This work extends an investigation into the use of a cavity flameholder to aid scramjet combustion at high flight Mach number. A parallel scramjet duct incorporating a cavity flameholder in the floor with an inclined rear face and an aspect ratio of 4.8 was investigated. The experiments were performed in a shock tunnel facility operated in semidirect- connect mode. Measurements of the axial pressure distribution along the floor of the duct were made and both planar laser induced fluorescence (PLIF) and luminosity images were recorded of the flow in the vicinity of the duct. The experiments described here were for a range of equivalence ratios for hydrogen injected axially upstream into the cavity from the rear ramp of the cavity. This paper discusses the comparison of pressure data with the luminosity images and with steady state CFD simulations of the flow in the scramjet duct. While agreement was reasonable, especially in the form of the centerline pressure distribution down the duct, the numerical predictions under predict the observed pressure levels. This may be indicative of both the uncertainty in the free stream flow state and the simplified chemistry model used. Additionally the steady state model can not capture the inherently unsteady nature observed for the flow field. Simulations at slightly lower flight Mach number indicate that combustion at these lower conditions is only marginal. The numerical simulations indicate that the pressure drag penalty incurred by the cavity can be reduced by the injection of fuel into the cavity and further again by the combustion of the fuel above the cavity.
Subjects 090107 Hypersonic Propulsion and Hypersonic Aerodynamics
Q-Index Code E1
Institutional Status Non-UQ
Additional Notes AIAA-2005-3358

 
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