Imaging of hydrogen fuel injection on the intake of a heated wall scramjet

Kovachevich, Anne L., Hajek, Kim M., McIntyre, Timothy J., Paull, Allan and Abdel-Jawad, Madhat (2006). Imaging of hydrogen fuel injection on the intake of a heated wall scramjet. In: 42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference Proceedings (2006). 42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference, Sacramento, California, (6886-6895). 9 - 12 July 2006.

Author Kovachevich, Anne L.
Hajek, Kim M.
McIntyre, Timothy J.
Paull, Allan
Abdel-Jawad, Madhat
Title of paper Imaging of hydrogen fuel injection on the intake of a heated wall scramjet
Conference name 42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference
Conference location Sacramento, California
Conference dates 9 - 12 July 2006
Convener American Institute of Aeronautics and Astronautics (AIAA)
Proceedings title 42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference Proceedings (2006)
Journal name Collection of Technical Papers - AIAA/ASME/SAE/ASEE 42nd Joint Propulsion Conference
Publisher AIAA
Publication Year 2006
Sub-type Fully published paper
Open Access Status Not yet assessed
ISBN 978-1-56347-818-5
Volume 9
Start page 6886
End page 6895
Total pages 10
Language eng
Abstract/Summary This paper discusses experiments performed in the T4 shock tunnel at the University of Queensland observing hydrogen injection onto the intake of a scramjet model. Cold wall intake experiments are compared with wall temperatures of up to 700K for experiments with a free-stream enthalpy of 3.6MJ/kg. Fluorescent imaging was used to view levels of nitric oxide and hydroxide radicals in the flow. Observation of nitric oxide was found to give a clear image of fuel jet penetration. The fuel jet penetration was observed when the intake was placed at an angle of 0.5 degrees to the free-stream and at 9 degrees to the free-stream. In the 9 degree case the fuel was seen to penetrate well beyond the boundary layer. No hydroxide was observed on the intake when wall temperatures were varied from 300K to 700K. Furthermore, no static pressure increase was observed along the model. These factors indicate that no combustion was occurring.
Subjects 090107 Hypersonic Propulsion and Hypersonic Aerodynamics
020501 Classical and Physical Optics
Q-Index Code EX
Additional Notes Paper ID: AIAA-2006-5039

Document type: Conference Paper
Sub-type: Fully published paper
Collections: Excellence in Research Australia (ERA) - Collection
School of Mathematics and Physics
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