Research on the Influence of the Unit Reynold’s Number on the Characteristics of N-Waves at M = 2.5
https://doi.org/10.25205/2541-9447-2021-16-1-53-64
Abstract
This paper presents the results of studying the features of the development of weak shock waves generated by a two-dimensional roughness on the wall of the working part of a supersonic wind tunnel in a free flow at a Mach number of 2.5. The measurements were performed with a constant resistance thermoanemometer. It is shown that a two-dimensional sticker induces weak shock waves into the free flow. They cause distortion of the average flow, the shape of which corresponds to the N-wave. High-intensity pulsations were recorded in the region of passage of a pair of weak shock waves. With an increase in the unit Reynolds number, the level of distortions of the average flow remains practically constant, but an increase in nonstationary disturbances is observed. It was found that the greatest increase in pulsations caused by Mach waves is observed in the area of the maximum gradient of the average flow. It is found that an increase in the number Re1 leads to an expansion of the frequency range of unstable disturbances generated by a pair of weak shock waves.
Supporting agencies: The work was carried out within the framework of the Program of Fundamental Scientific Research of the State Academies of Sciences for 2013-2020 (project АААА-А17-117030610125-7). The authors are grateful to the Center for collective use “Mechanics” for the provided equipment
About the Authors
Yu. I. Usynina
Khristianovich Institute of Theoretical and Applied Mechanics SB RAS; Novosibirsk State Technical University
Russian Federation
Russian Federation
Yulia I. Usynina, Laboratory Assistant, Khristianovich Institute of Theoretical and Applied Mechanics SB RAS; Student, Novosibirsk State Technical University
Novosibirsk
Yu. G. Yermolaev
Khristianovich Institute of Theoretical and Applied Mechanics SB RAS; Novosibirsk State University
Russian Federation
Russian Federation
Yury G. Yermolaev, PhD, Senior Fellow, Khristianovich Institute of Theoretical and Applied Mechanics SB RAS; Teaching Assistant, Novosibirsk State University
Novosibirsk
A. D. Kosinov
Khristianovich Institute of Theoretical and Applied Mechanics SB RAS; Novosibirsk State University
Russian Federation
Russian Federation
Alexander D. Kosinov, Doctor of Science (Physics and Mathematics), Senior Researcher, Head of Laboratory, Khristianovich Institute of Theoretical and Applied Mechanics SB RAS; Professor, Novosibirsk State University
Novosibirsk
N. V. Semionov
Khristianovich Institute of Theoretical and Applied Mechanics SB RAS
Russian Federation
Russian Federation
Nikolai V. Semionov, Doctor of Science (Physics and Mathematics), Senior Researcher, Leading Researcher
Novosibirsk
References
1. Gaponov S. A., Maslov A. A. Development of perturbations in compressible flows. Novosibirsk, Nauka, 1980, 134 p. (in Russ.)
2. Laufer J. Aerodynamic noise in supersonic wind tunnels. Aerospase Sci., 1961, vol. 28, no. 9, p. 685−692.
3. Semionov N. V. An experimental study of receptivity of supersonic boundary layer on a blunted plate. In: Proc. 6 th IASME / WSEAS International Conference on Fluid Mechanics and Aerodynamics. WSEAS Press, 2008. P. 119–124.
4. Gaponov S. A., Semenov A. N. Numerical simulation of the interaction of a supersonic boundary layer with an acoustic wave. Fluid Dynamics, 2018, no. 6, p. 76–86. (in Russ.)
5. Borovoi V. Y., Egorov I. V., Noev A. Y., Skuratov A. S., Struminskaya I. V. Two-dimensional interaction between an incident shock and a turbulent boundary layer in the pre sence of an entropy layer. Fluid Dynamics, 2011, vol. 46, no. 6, p. 917–934.
6. Paul K. Chang. Separation of flow. Moscow, Mir, 1972, vol. 1; 1973. vol. 2, 3. (in Russ.)
7. Green J. E. Interactions between shock waves and turbulent boundary layers. Progr. Aerospace Sci., 1970, vol. 11, p. 235–340.
8. Delery J. Shock wave / turbulent boundary layer interaction and its control. Progr. Aerospace Sci., 1985, vol. 22, p. 209–280.
9. Knight D., Yan H., Panaras A. G., Zheltovodov A. Advances in CFD prediction of shock wave turbulent boundary layer interactions. Progr. Aerospace Sci., 2003, vol. 39, no. 2–3, p. 121–184.
10. Fedorova N. N., Fedorchenko I. A. Computations of interaction of an incident oblique shock wave with a turbulent boundary layer on a flat plate. Journal of Applied Mechanics and Technical Physics, 2004, vol. 45, no. 3, p. 358–366.
11. Polivanov P. A., Sidorenko A. A., Maslov A. A. The influence of the laminar-turbulent transition on the interaction between the shock wave and boundary layer at a low supersonic Mach number. Technical Physics Letters, 2015, vol. 41, no. 19, p. 933–937.
12. Vaganov A. V., Ermolaev Yu. G., Kolosov G. L., Kosinov A. D., Panina A. V., Semionov N. V. Impact of an incident mach wave on the fluctuation field in the boundary layer on a plane delta wing. Vestnik NSU. Series: Physics, 2014, vol. 9, no. 1, p. 29–38. (in Russ.)
13. Vaganov A. V., Yermolaev Y. G., Kosinov A. D., Semionov N. V., Shalaev V. I. Experimental study of flow structure and transition in the boundary layer of a delta wing with blunted leading edges at Mach numbers 2, 2.5 and 4. Proceedings of the MIPT, 2013, vol. 5, no. 3, p. 164–173.
14. Vaganov A. V., Ermolaev Yu. G., Kolosov G. L., Kosinov A. D., Panina A. V., Semionov N. V. Impact of incident mach wave on supersonic boundary layer. Thermophysics and Aeromechanics, 2016, vol. 23, no. 1, p. 45–50.
15. Yermolaev Yu. G., Yatskih A. A., Kosinov A. D., Semionov N. V., Kolosov G. L., Panina A. V. Experimental study of the effects of couple weak waves on laminar-turbulent transition on attachment-line of a swept cylinder. AIP Conf. Proc., 2016., vol. 1770, p. 020012.
16. Kosinov A. D., Golubev M. P., Pavlov Al. A. On the determination of the mechanism of the interaction between mach waves and a bow shock wave. Siberian Journal of Physics, 2017, vol. 12, no. 2, p. 20–27 (in Russ.)
17. Vaganov A. V., Kosinov A. D., Noev A. Yu., Radchenko V. N., Skuratov A. S. Regimes of flow turbulization near swept wing edge in hypersonic flow. AIP Conf. Proc., 2018, vol. 2027, no. 1, p. 030112.
18. Ermolaev Yu. G., Kosinov A. D., Kocharin V. L., Semenov N. V., Yatskikh A. A. Experimental investigation of the weak shock wave influence on the boundary layer of a flat blunt plate at the Mach number 2.5. Fluid Dynamics, 2019, vol. 54, no. 2, p. 257–263.
19. Kosinov A. D., Semionov N. V., Yatskikh A. A., Yermolaev Yu. G., Piterimova M. V. Experimental study of effect of weak shock waves on supersonic boundary layer of flat plate with blunt leading edge at mach number 2. Siberian Journal of Physics, 2018, vol. 13, no. 3, p. 16–23.
20. Yatskikh A. A., Kosinov A. D., Semionov N. V., Smorodsky B. V., Ermolaev Yu. G., Kolosov G. L. Investigation of laminar-turbulent transition of supersonic boundary layer by scanning constant temperature hot-wire anemometer. In: XIX International Conference on the Methods of Aerophysical Research (ICMAR 2018). AIP Conference Proceedings, 2018, vol. 2027, no. 1, p. 040041(5).
Review
For citations:
Usynina Yu.I., Yermolaev Yu.G., Kosinov A.D., Semionov N.V. Research on the Influence of the Unit Reynold’s Number on the Characteristics of N-Waves at M = 2.5. SIBERIAN JOURNAL OF PHYSICS. 2021;16(1):53-64. (In Russ.) https://doi.org/10.25205/2541-9447-2021-16-1-53-64
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