This note reports tests in a shock tunnel in which a fully integrated scramjet configuration produced net thrust. The experiments not only showed that impulse facilities can be used for assessing thrust performance, but also were a demonstration of the application of a new technique to the measurement of thrust on scramjet configurations in shock tunnels. These two developments are of significance because scramjets are expected to operate at speeds well in excess of 2 km/sec, and shock tunnels offer a means of generating high Mach number flows at such speeds.


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    Titel :

    Scramjet thrust measurement in a shock tunnel


    Beteiligte:
    Paull, A. (Autor:in) / Stalker, R. J. (Autor:in) / Mee, D. J. (Autor:in)


    Erscheinungsdatum :

    1995-01-01


    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Scramjet thrust measurement in a shock tunnel

    Paull, A. / Stalker, R. J. / Mee, D. J. | NTRS | 1995


    Scramjet thrust measurement in a shock tunnel

    Paull, A. | Online Contents | 1995


    Measurement of scramjet thrust in shock tunnels

    Stalker, R. / Simmons, J. / Paull, A. et al. | AIAA | 1994


    Measurement of Scramjet Thrust in Shock Tunnels

    Stalker, R. J. / Simmons, J. M. / Paull, A. et al. | British Library Conference Proceedings | 1994


    Measurements of Scramjet Thrust in Shock Tunnels

    R. J. Stalker / J. M. Simmons / A. Paull et al. | NTIS | 1995