A mathematical model of the heat protective coating mass ablation is formed to determine the necessary thickness of the coating under conditions of total stagnation of the gas-dynamic flow on the coating surface. The maximal linear loss of heat protective coating mass and the necessary thickness of the coating at the total stagnation point were determined. A line was revealed to improve the accuracy of the mathematical model of the heat protective coating mass loss and reduce the number of assumptions adopted in the calculation.


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    Titel :

    Assessing the Applicability of Ablative Thermal Protection Coating for an Ultralight Launch Vehicle


    Weitere Titelangaben:

    Russ. Aeronaut.


    Beteiligte:
    Vaulin, S. D. (Autor:in) / Tret’yakov, P. A. (Autor:in) / Peshkov, R. A. (Autor:in) / Mikhailov, E. A. (Autor:in)

    Erschienen in:

    Russian Aeronautics ; 66 , 4 ; 683-690


    Erscheinungsdatum :

    01.12.2023


    Format / Umfang :

    8 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch




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