Difference schemes in computations for chemically non-equilibrium processes in the rocket engine nozzles

Difference schemes in computations for chemically non-equilibrium processes in the rocket engine nozzles

The problem of determining the “potential” number of integration steps by explicit difference schemes is solved within the framework of the prediction model for chemically non-equilibrium processes.

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Bibliographische Detailangaben
Veröffentlicht in:Russian aeronautics 2017, Vol.60 (1), p.103-109
Hauptverfasser: Kryukov, V. G., Abdullin, A. L., Demin, A. V.
Format: Artikel
Sprache:eng
Schlagworte:
Aircraft and Rocket Engine Design and Development
Automotive Engineering
Engineering
Nozzles
Organic chemistry
Rocket engines
Rockets
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Beschreibung
Zusammenfassung:The problem of determining the “potential” number of integration steps by explicit difference schemes is solved within the framework of the prediction model for chemically non-equilibrium processes.
ISSN:1068-7998
1934-7901
DOI:10.3103/S1068799817010159