Three-dimensional finite rate chemistry solutions are performed on a single fuel injector configuration. The results are compared with limited experimental data obtained from the HYPULSE expansion tube facility at simulated flight Mach 17 flow conditions. All comparisons, except for wall heat flux, were in excellent agreement. Key findings from this study are useful in interpretation of the experimental measurements.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    CFD evaluation of Mach 17 HYPULSE scramjet combustor data


    Beteiligte:

    Erscheinungsdatum :

    01.12.1991


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch




    CFD evaluation of Mach 17 HYPULSE scramjet combustor data

    BOBSKILL, GLENN / BITTNER, ROBERT / RIGGINS, DAVID et al. | AIAA | 1991


    Mach 12 & 15 Scramjet Test Capabilities of the HYPULSE Shock-Expansion Tunnel

    Hass, N. E. / Shih, A. T. / Rogers, R. C. et al. | British Library Conference Proceedings | 2005


    Expansion of the scramjet ground test envelope of the Hypulse facility

    Bakos, R. / Castrogiovanni, A. / Calleja, J. et al. | AIAA | 1996


    Scramjet Combustor

    Musielak, Dora | Wiley | 2022


    Scramjet Combustor Characteristics at Hypervelocity Condition over Mach 10 Flight

    Takahashi, M. / Komuro, T. / Sato, K. et al. | British Library Conference Proceedings | 2009