Comparison of Computational and Experimental Studies on Shock Induced Ignition in Scramjets

McGuire, Jeff, Boyce, Russell and Mudford, Neil (2005). Comparison of Computational and Experimental Studies on Shock Induced Ignition in Scramjets. In: A Collection of Technical Papers - 13th AIAA/CIRA International Space Planes and Hypersonic Systems and Technologies Conference. AIAA/CIRA 13th International Space Planes and Hypersonics Systems and Technologies Conference, Capua, Italy, (1637-1652). 16-20 May 2005.


Author McGuire, Jeff
Boyce, Russell
Mudford, Neil
Title of paper Comparison of Computational and Experimental Studies on Shock Induced Ignition in Scramjets
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 A Collection of Technical Papers - 13th AIAA/CIRA International Space Planes and Hypersonic 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 1637
End page 1652
Total pages 16
Language eng
Abstract/Summary Due to the problems associated with rapid mixing of fuel in scramjet engines, attempts are now being made to inject the fuel on the intake ramp so that it is well mixed by the time it enters the combustor. This however requires a reduced compression on the intake to ensure the flow does not ignite before it reaches the combustor. Once in the combustor, the flow is then ignited via shock waves generated from the engine cowl. This paper initially examines the ignition characteristics of a simple 2-D premixed hydrogen/air flow through a duct of constant height to determine the mechanisms responsible for radical production and heat release. Results are then reported for computed 2D scramjet combustion chamber flows of premixed hydrogen and air. Results of a 3D CFD calculation without fuel injection are also presented, and compared with experimental data obtained from the T3 shock tunnel at the Australian National University. Experimental data is also presented for a scramjet flow with combustion
Subjects 090107 Hypersonic Propulsion and Hypersonic Aerodynamics
Q-Index Code E1
Institutional Status Non-UQ
Additional Notes AIAA 2005-3394

 
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