About the Relationship between Disturbances in a Free Supersonic Flow and Disturbances in a Boundary Layer at Mach Number 2
https://doi.org/10.25205/2541-9447-2020-15-2-50-60
Abstract
An experimental study of the effect of pulsations of free supersonic flow on the pulsations of the boundary layer of a flat plate with a sharp edge using a new three-channel hot-wire anemometer measurement system is carried out. The spatial-temporal distributions of the correlation coefficient are obtained for the boundary layer cross sections and for the laminar-turbulent transition region.
Keywords
experiment,
supersonic flows,
constant temperature hot-wire anemometer,
correlation coefficient,
relationship
Supporting agencies: The research was carried out within the framework of the Program of Fundamental Scientific Research of the state academies of sciences in 2013-2020 (project No. AAAA-A17-117030610125-7). Experiments were carried out using the equipment of the Joint Access Center “Mechanics”.
About the Authors
L. V. Afanasev
Khristianovich Institute of Theoretical and Applied Mechanics SB RAS;
Novosibirsk State University
Russian Federation
Russian Federation
Leonid V. Afanasev, laboratory assistant
Novosibirsk
A. D. Kosinov
Khristianovich Institute of Theoretical and Applied Mechanics SB RAS;
Novosibirsk State University
Russian Federation
Russian Federation
Aleksandr D. Kosinov, Doctor of Science (Physics and Mathematics), senior researcher
Novosibirsk
Yu. G. Yermolaev
Khristianovich Institute of Theoretical and Applied Mechanics SB RAS;
Novosibirsk State University
Russian Federation
Russian Federation
Yuri G. Yermolaev, PhD, senior researcher
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. Mack L. M. Linear Stability Theory and the Problem of Supersonic Boundary Layer Transition. AIAA Journal, 1975, vol. 13 (3), p. 278–289.
2. Кеdall J. M. Wind Tunnel Experiments Relating to Supersonic and Hypersonic BoundaryLayer Transition. AIAA Journal, 1975, vol. 13 (3), p. 290–299.
3. Jones G. S., Stainback P. C., Harris C. D., Brooks C. W., Clukey S. J. Flow Quality Measurements for the Langley 8-Foot Transonic Pressure Tunnel LFC Experiment. In: AIAA-890150, 1989.
4. Lebiga V. A., Zinoviev V. N., Pak A. Yu. The use of a hot-wire anemometer for measuring the characteristics of an arbitrary acoustic field in compressible flows. Journal of Applied Mechanics and Technical Physics, 2020, vol. 43, no. 3, p. 176–181. (in Russ.)
5. Frenkiel F. N., Klebanoff P. S. Correlation Measurement in a Turbulent Flow using High Speed Computing Methods. The Physics of Fluids, 1967, no. 10, p. 1737.
6. Afanasev L. V., Kocharin V. L., Yatskikh A. A., Kosinov A. D., Semionov N. V., Yermolaev Yu. G., Kolosov G. L. The correlation of the pulsations of flow in the settling chamber with the pulsations of supersonic flow. J. Phys.: Conf. Ser., 2019, vol. 1404, p. 012074.
7. Yatskikh A. A., Kosinov A. D., Semionov N. V., Smorodsky B. V., Ermolaev Y. G., Kolosov G. L. Investigation of laminar-turbulent transition of supersonic boundary layer by scanning constant temperature hot-wire anemometer. In: AIP Conf. Proc., 2018, vol. 2027 (1), p. 040041.
8. Kosinov A. D., Semisynov A. I. Character of Evolution of Natural Disturbances in a Supersonic Boundary Layer on a Flat Plate. Teplofiz. Aeromekh., 2003, vol. 10 (1), p. 41–46. [Thermophys. Aeromech., 2003, vol. 10 (1), p. 39–44].
9. Kosinov A. D., Semisynov A. I. Using of high-order spectral analysis and statistical features of disturbances for investigation of nonlinear stages of transition in supersonic boundary layer. Preprint.
10. Kocharin V. L., Afanasev L. V., Kosinov A. D., Yatskikh A. A., Semionov N. V., Yermolaev Yu. G. Experimental investigation of effect of an external wave on supersonic boundary layer of the blunt flat plate. In: AIP Conf. Proc., 2019, vol. 2125 (030104), p. 1–6.
11. Kocharin V. L., Kosinov A. D., Yatskikh A. A., Afanasev L. V., Ermolaev Yu. G., Semionov N. V. The experimental study of the weak shock wave action on the boundary layer of the sweep flat plate. J. Phys.: Conf. Ser., 2019, vol. 1404 (012083), p. 1–4.
12. Kocharin V. L., Kosinov A. D., Yatskikh A. A., Ermolaev Yu. G., Semionov N. V., Piterimova M. V., Shevelkov S. G., Minin O. P. The impact of weak shock waves on the flow in the boundary layer of a flat plate with a variable sweep angle of the leading edge. Thermophysics and Aeromechanics, 2019, vol. 26 (6), p. 803–809.
13. Kocharin V. L., Semionov N. V., Kosinov A. D., Yermolaev Yu. G., Yatskikh A. A. Experimental study of effect of a couple of weak shock waves on boundary layer of the blunt flat plate. In: AIP Conf. Proc., 2018, vol. 2027, p. 040026.
14. Yermolaev Yu. G., Kosinov A. D., Kocharin V. L., Semionov N. V., Yatskih 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 (2), p. 257–263.
Review
For citations:
Afanasev L.V., Kosinov A.D., Yermolaev Yu.G., Semionov N.V. About the Relationship between Disturbances in a Free Supersonic Flow and Disturbances in a Boundary Layer at Mach Number 2. SIBERIAN JOURNAL OF PHYSICS. 2020;15(2):50-60. (In Russ.) https://doi.org/10.25205/2541-9447-2020-15-2-50-60
Views:
139
Email this article 