Research has been conducted for a number of years at the NASA Langley Research Center to develop a supersonic combustion ramjet (scramjet) capable of propelling a vehicle at hypersonic speeds in the atmosphere or beyond. Recently, that research has been directed toward the optimization of the scramjet combustor, and in particular the efficiency of fuel-air mixing and reaction in the engine. This paper describes a study of fuel-air mixing and reaction in a supersonic flow field, and discusses several techniques that were applied for enhancing the mixing processes and overal combustion efficiency in the flow. Based on the results of the study, an alternate fuel injector configuration was computationally designed, and that configuration significantly increased the amount of fuel-air mixing and combustion over a given combustor length that was achieved.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Mixing and combustion enhancement in supersonic reacting flows


    Beteiligte:

    Kongress:

    International Symposium on Numerical Methods in Engineering


    Erscheinungsdatum :

    01.01.1989


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Shock-Induced Mixing Enhancement of Supersonic Turbulent Reacting Ramjet Flows

    Hong, Z.-C. / Shih, M.-S. / International Astronautical Federation | British Library Conference Proceedings | 1995


    Mixing and Mixing Enhancement in Supersonic Reacting Flowfields

    Curran, E. T. / Murthy, S. N. B. | AIAA | 1991


    Analysis of losses in supersonic mixing and reacting flows

    RIGGINS, D. / MCCLINTON, C. | AIAA | 1991


    Research on Supersonic Reacting Flows

    Bowman, C. T. et al / Air Force Office of Scientific Research | British Library Conference Proceedings | 1994