Non-uniqueness of transonic flow in an intake-type channel

Research output


The two-dimensional turbulent airflow in a 9-degrees-bent channel is studied numerically. Inner surfaces of the top and bottom walls are parallel to each other upstream and downstream of the bend. The free stream is supersonic, whereas the flow is subsonic at the channel exit. Solutions of the Reynolds-averaged Navier-Stokes equations are obtained with a finite-volume solver using the Spalart-Allmaras and Shear Stress Transport k-! turbulence models. The solutions reveal a flow hysteresis and non-uniqueness in considerable bands of the free-stream Mach number, angle of attack, and exit pressure. At the endpoints of the bands, there are abrupt changes of the shock wave system. The non-uniqueness admits different losses of the total pressure, which may cause different trusts of an air breathing engine.

Original languageEnglish
Article number012012
Number of pages6
JournalJournal of Physics: Conference Series
Issue number1
Publication statusPublished - 13 Dec 2019
Event4th International Conference on Supercomputer Technologies of Mathematical Modelling, SCTeMM 2019 - Moscow
Duration: 19 Jun 201921 Jun 2019

Scopus subject areas

  • Physics and Astronomy(all)

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