Flat panels of carbon/carbon-silicon carbide and carbon/carbon were installed downstream of a hydrogen-fueled dual-mode scramjet combustor and tested for several minutes at conditions simulating flight at Mach 5 and Mach 6. The most severe test involved a carbon/carbon-silicon carbide panel that experienced three cycles totaling over 153 s at Mach 6 enthalpy, with fueling at an equivalence ratio of 1.0 for 118 s. Based on embedded thermocouple measurements and one-dimensional transient thermal analysis, the inside wall temperature was calculated to reach a maximum of 1400°C during the test program. Both the carbon/carbon-silicon carbide and carbon/carbon panels experienced minimal erosion during the tests, giving strong confidence that both would be a viable material system for use in a scramjet combustor for short-duration test flights.


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    Title :

    Testing of Refractory Composites for Scramjet Combustors



    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



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