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

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....

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Veröffentlicht in:	Russian aeronautics 2017-10, Vol.60 (4), p.600-608
Hauptverfasser:	Molchanov, A. M., Myakochin, A. S.
Format:	Artikel
Sprache:	eng
Schlagworte:	Aircraft and Rocket Engine Theory Automotive Engineering Engineering
Online-Zugang:	Volltext
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