A new solution method is proposed to solve the one-dimensional transonic reacting flows of a scramjet combustor, which represents a mathematical singularity in the governing equations when the flow velocity approaches the speed of sound. The governing equations of the one-dimensional transonic flows are rewritten by using a variable transformation method and, in this way, the singularity of the governing equations is eliminated. Subsequently, a forward iterative shooting method is introduced to deal with the numerical problem appearing in the flow that includes finite-rate chemistry and high-temperature gas properties. Comparative analysis is performed to evaluate the method presented in this paper and previous methods. The results show that it has a wider applicability and better stability in solving the one-dimensional transonic reacting flows than previous methods. One major advantage of this method is that, as a result of the elimination of the singularity using variable transformation and the introduction of a forward iterative shooting method, a smooth and stable numerical calculation for transonic reacting flows can be ensured.


    Access

    Access via TIB

    Check availability in my library

    Order at Subito €


    Export, share and cite



    Title :

    New Method for Solving One-Dimensional Transonic Reacting Flows of a Scramjet Combustor



    Published in:

    Publication date :

    2016




    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English



    Classification :

    BKL:    55.50 Luftfahrzeugtechnik / 55.50
    Local classification TIB:    770/7040






    One Dimensional Modelling of a Scramjet Combustor Reacting Flow

    Scheuermann, T. / Chun, J. / von Wolfersdorf, J. et al. | British Library Conference Proceedings | 2008


    3-D numerical simulation of supersonic reacting flows in scramjet combustor

    Liang, J. / Wang, C. | British Library Online Contents | 1998