OH visualization of ethylene combustion modes in the exhaust of a fundamental, supersonic combustor

This work examined combustion modes in a fundamental, axisymmetric, supersonic combustor at flight equivalent Mach numbers ranging from 7.5 to 9.0. Ethylene was injected at a variety of mass flow rates to examine both scram-mode, jet wake stabilized and dual-mode combustion. At higher flight Mach nu...

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Veröffentlicht in:	Combustion and flame 2021-04, Vol.226, p.143-155
Hauptverfasser:	Vanyai, Tristan, Landsberg, Will O., McIntyre, Timothy J., Veeraragavan, Ananthanarayanan
Format:	Artikel
Sprache:	eng
Schlagworte:	Centroids Clusters Combustion chambers Cross-sections Equivalence ratio Ethylene Flow visualization Hypersonic propulsion Mach number Mass flow rate Planar laser induced fluorescence Supersonic combustion Supersonic combustion ramjet engines
Online-Zugang:	Volltext
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