A numerical study is carried out to investigate the shock-induced combustion in premixed hydrogen-air mixture. The calculations have been carried out for Mach 5.11 and 6.46. The Mach 5.11 case was found to be unsteady with periodic oscillations. The frequency of oscillations was calculated and was found to be in good agreement with the experimentally observed frequency. The Mach 6.46 case was found to be of a very high frequency and very low-amplitude phenomena. This supports the existing view that it is possible to stabilize the shock-induced combustion phenomena with sufficient level of overdrive.
Hypersonic shock-induced combustion in a hydrogen-air system
Hyperschall stoßwelleninduzierte Verbrennung in einem Wasserstoff-Luft System
AIAA Journal ; 33 , 1 ; 173-176
1995
4 Seiten, 5 Bilder, 16 Quellen
Aufsatz (Zeitschrift)
Englisch
Hypersonic Shock-Induced Combustion in a Hydrogen-Air System (TN)
| Online Contents | 1995
Hypersonic Shock-Induced Combustion Propulsion
| British Library Conference Proceedings | 2009
Hypersonic Shock-Induced Combustion Propulsion
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