A free-piston shock tunnel has been used to obtain test data on a scramjet combustion chamber with sidewall injection. The results obtained indicate that combustion was strongly influenced by a region of fuel whose temperature was held below its ignition temperature by wall-cooling effects; this increased the fraction of unburned fuel and resulted in a significant loss of specific impulse. Aerodynamic heating would keep the walls above hydrogen ignition temperature in an actual scramjet powerplant, however. Maximum specific impulse was obtained with a combination of parallel and transverse injection in a long combustion chamber, followed by a dual stage expansion.


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    Titel :

    Hydrogen scramjet with sidewall injection - Shock tunnel simulations


    Beteiligte:
    Morgan, R. G. (Autor:in) / Paull, A. (Autor:in) / Morris, N. (Autor:in) / Stalker, R. J. (Autor:in)

    Erscheinungsdatum :

    1987-01-01


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch





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