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Hysteresis of oscillatory airflow in a supersonic intake model

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Abstract

Supersonic airflow deceleration in a conventional mixed-compression intake is studied numerically. The simulation of turbulent two-dimensional flow is based on the Reynolds-averaged Navier–Stokes equations and the k-ω SST turbulence model. Numerical solutions are obtained with ANSYS-18.2 CFX finite-volume solver of second-order accuracy. The solutions reveal flow hysteresis with step-by-step changes in the free-stream Mach number M∞. The hysteresis is caused by the instability of an interaction of a shock wave with the local region of flow acceleration formed near the throat of intake. Oscillations of the Mach number M∞ in time are considered as well, and the existence of hysteresis is confirmed at small values of the amplitude A and period τ of the oscillations. The hysteresis shrinks with increasing amplitude A and eventually disappears at sufficiently large amplitudes. The dependence of shock wave oscillations on the period τ is also studied and transitions between different flow regimes are discussed.

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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.

References

  1. Shedon J (1999) Intake aerodynamics. Blackwell Publishing Ltd., London

    Google Scholar 

  2. Panchal D, Chhayani D (2021) Review paper on the unstarting of the supersonic air intake. Int J Eng Res Technol 10(12). https://www.ijert.org/review-paper-on-the-unstarting-of-the-supersonic-air-intake

  3. Kusunose K, Matsushima K, Maruyama D (2011) Supersonic biplane—a review. Prog Aerosp Sci 47:53–87. https://doi.org/10.1016/j.paerosci.2010.09.003

    Article  Google Scholar 

  4. Yamashita H, Kuratani N, Yonezawa M, Ogawa T, Nagai H, Asai K, Obayashi S (2013) Wind tunnel testing on start/unstart characteristics of finite supersonic biplane wing. Int J Aerosp Eng Hindawi. https://doi.org/10.1155/2013/231434. (Article 231434)

    Article  Google Scholar 

  5. Guo S, Wang Z, Zhao Y (2014) The flow hysteresis in the supersonic curved channel. J Natl Univ Defense Technol 36(4):10–14

    MathSciNet  Google Scholar 

  6. Li T (2015) Study on hysteresis phenomenon caused by back pressure in curved isolator. Master’s Thesis, National University of Defense Technology, Changsha, China

  7. Feng S, Chang J, Zhang Ch, Wang Y, Ma J, Bao W (2017) Experimental and numerical investigation on hysteresis characteristics and formation mechanism for a variable geometry dual-mode combustor. Aerosp Sci Technol 67:96–104. https://doi.org/10.1016/j.ast.2017.03.040

    Article  Google Scholar 

  8. Feng S, Chang J, Zhang Y, Zhang Ch, Wang Y, Bao W (2017) Numerical studies for performance improvement of a variable geometry dual mode combustor by optimizing deflection angle. Aerosp Sci Technol 68:320–330. https://doi.org/10.1016/j.ast.2017.05.025

    Article  Google Scholar 

  9. Das S, Prasad JK (2010) Starting characteristics of a rectangular supersonic air intake with cowl deflection. Aeronaut J 114:177–189. https://doi.org/10.1017/S0001924000003626

    Article  Google Scholar 

  10. Jin Y, Sun S, Tan H, Zhang Y, Huang H (2022) Flow response hysteresis of throat regulation process of a two-dimensional mixed-compression supersonic inlet. Chin J Aeronaut 35(3):112–127. https://doi.org/10.1016/j.cja.2021.06.013

    Article  Google Scholar 

  11. Tang X, Fan X, Xiong B, Chen L, Chen J (2023) Study of multiple solution phenomenon for hypersonic air inlet. Aerosp Sci Technol 136:Article 108236. https://doi.org/10.1016/j.ast.2023.108236

    Article  Google Scholar 

  12. Jiao X, Chang J, Wang Zh, Yu D (2016) Hysteresis phenomenon of hypersonic inlet at high Mach number. Acta Astronaut 128:657–668. https://doi.org/10.1016/j.actaastro.2016.08.025

    Article  Google Scholar 

  13. Kuzmin A (2019) Shock wave instability in a bent channel with subsonic/supersonic exit. Adv Aircr Spacecr Sci 6(1):19–30. https://doi.org/10.12989/aas.2019.6.1.019

    Article  Google Scholar 

  14. Kuzmin A (2019) Non-uniqueness of transonic flow in an intake-type channel. J Phys Conf Ser 1392:Article ID 012012, 1–6. https://doi.org/10.1088/1742-6596/1392/1/012012

    Article  Google Scholar 

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

    Article  Google Scholar 

  16. ANSYS Fluids (2023) Computational fluid dynamics. https://www.ansys.com/products/fluids. Accessed 18 Oct 2023

  17. Tennekes H, Lumley JL (1992) A first course in turbulence (14. print. ed.). MIT Press, Cambridge

    Google Scholar 

  18. Menter FR (2009) Review of the shear-stress transport turbulence model experience from an industrial perspective. Int J Comput Fluid Dyn 23:305–316. https://doi.org/10.1080/10618560902773387

    Article  Google Scholar 

  19. Kuzmin A, Babarykin K (2018) Supersonic flow bifurcation in twin intake models. Adv Aircr Spacecr Sci 5(4):445–458. https://doi.org/10.12989/aas.2018.5.4.445

    Article  Google Scholar 

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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 Grant No. 2304-084 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. Hysteresis of oscillatory airflow in a supersonic intake model. AS (2024). https://doi.org/10.1007/s42401-023-00268-9

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  • DOI: https://doi.org/10.1007/s42401-023-00268-9

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