An ablative material composed of silica-filled elastomeric silicone was tested to evaluate its thermal and structural performance as an external insulator, or heat shield, for a hypersonic research aircraft. The material was also tested to determine whether it would form a durable char layer when initially heated and thereafter function primarily as an insulator with little further pyrolysis or char removal. Aerothermal tests were representative of nominal Mach 6 cruise conditions of the aircraft, and additional tests were representative of Mach 8 cruise and interference heating conditions. Radiant heating tests were used to simulate the complete nominal Mach 6 surface-temperature history. The silica char that formed during aerothermal tests was not durable. The char experienced a general and preferential surface recession, with the primary mechanism for char removal being erosion. Tests revealed that radiant heating is not a valid technique for simulating aerodynamic heating of the material.


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    Titel :

    Experimental performance of an ablative material as an external insulator for a hypersonic research aircraft


    Beteiligte:
    Puster, R. L. (Autor:in) / Chapman, A. J. (Autor:in)

    Erscheinungsdatum :

    1977-11-01


    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch







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