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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    Title :

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


    Additional title:

    Russ. Aeronaut.


    Contributors:

    Published in:

    Russian Aeronautics ; 66 , 4 ; 683-690


    Publication date :

    2023-12-01


    Size :

    8 pages




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English




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