Abstract A method for numerical simulation of the combustion of hydrogen in a supersonic air flow is developed. Comparison of the calculation results with the experimental data showed a satisfactory agreement. The calculation results using the nonequilibrium and equilibrium techniques differ from each other. It is shown that combustion parameters substantially depend on the geometric characteristics of the inlet device, the combustion chamber and the nozzle.


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    Title :

    Numerical Simulation of the Flow in the Scramjet Combustion Chamber Taking into Account Nonequilibrium Chemical Reactions


    Contributors:

    Published in:

    Russian Aeronautics ; 60 , 4 ; 600-608


    Publication date :

    2017-10-01


    Size :

    9 pages




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English





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