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Non-unique regimes of oscillatory transonic flow in bent channels

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Abstract

The turbulent transonic two-dimensional airflow in 9°-bent channels is studied numerically on the basis of the Reynolds-averaged Navier–Stokes equations. The flow is supersonic at the entrance of channels and subsonic at the exit. Numerical solutions reveal non-uniqueness of flow regimes in certain ranges of boundary conditions. The location of a formed shock wave exhibits hysteresis with changes in the inflow Mach number M∞, or the angle of attack, or pressure given at the exit pexit. The existence of hysteresis is caused by an interaction of the shock wave with an expansion flow region over the convex wall of channel. Shock wave behavior under forced oscillations of the Mach number M∞ or pressure pexit is discussed. Dependencies of hysteresis and non-unique regimes on the amplitude and period of the oscillations of M∞, pexit are studied. It is shown that hysteresis in a long channel is essentially wider than that in a short one.

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The author declares that the data supporting the findings of this study are available within the paper, and any supplementary information is available from the author on reasonable request.

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Acknowledgements

This research was performed using computational resources provided by the Computational Center of St. Petersburg State University (http://cc.spbu.ru).

Funding

The work was supported by a grant no. 92211015 from St. Petersburg State University.

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Authors and Affiliations

  1. Department of Fluid Dynamics, St. Petersburg State University, St. Petersburg, Russia

    Alexander Kuzmin

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  1. Alexander Kuzmin
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Correspondence to Alexander Kuzmin.

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Kuzmin, A. Non-unique regimes of oscillatory transonic flow in bent channels. AS (2023). https://doi.org/10.1007/s42401-023-00243-4

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