Mathematical simulation of hydrogen-oxygen combustion in rocket engines using LOGOS code

摘要

Hydrogen-oxygen fuels are very attractive now for rocket engines designers, because this pair is ecology friendly. Computer aided design of new effective and clean hydrogen engines needs mathematical tools for supercomputer modeling of hydrogen-oxygen components mixing and combustion in rocket engines. The paper presents the results of developing, verification and validation of mathematical model making it possible to simulate unsteady processes of ignition and combustion in rocket engines.