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.


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    Title :

    Hypersonic shock-induced combustion in a hydrogen-air system


    Additional title:

    Hyperschall stoßwelleninduzierte Verbrennung in einem Wasserstoff-Luft System


    Contributors:
    Ahuja, J.K. (author) / Tiwari, S.N. (author) / Singh, D.J. (author)

    Published in:

    AIAA Journal ; 33 , 1 ; 173-176


    Publication date :

    1995


    Size :

    4 Seiten, 5 Bilder, 16 Quellen




    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English




    Hypersonic shock-induced combustion in a hydrogen-air system

    Ahuja, J. K. / Tiwari, S. N. / Singh, D. J. | AIAA | 1995



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