Open AccessChoice of boundary conditions at the unsteady modeling of jets flowing into the supersonic flow
Author(s) -
V. P. Zamuraev,
А. П. Калинина,
D. S. Popova,
D. V. Fedorova,
О. Н. Иванова
Publication year - 2019
Publication title -
journal of physics. conference series
Language(s) - English
Resource type - Journals
SCImago Journal Rank - 0.21
H-Index - 85
eISSN - 1742-6596
pISSN - 1742-6588
DOI - 10.1088/1742-6596/1268/1/012024
Subject(s) - transonic , mechanics , supersonic speed , bandwidth throttling , shock wave , ignition system , jet (fluid) , choked flow , flow (mathematics) , rotational symmetry , physics , materials science , aerodynamics , thermodynamics , gas compressor
Numerical simulation of ignition of the gas mixture not mixed previously in the supersonic flow localized in a channel was performed. The ignition is initiated by the shock wave from the throttling jet, which results in significant changing of pressure difference between the main flow and the gas generator of the throttling jet. It is shown that applying boundary conditions similar to the breakdown of arbitrary discontinuity conditions, makes it possible to obtain the transonic mode observed in the experiment. The near-wall and axisymmetric supply of the gaseous fuel was considered.