Control of the Laminar-Turbulent Transition on the Wing Profile by Distributed Suction through a Finely Perforated Surface
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The results of experimental investigations of the influence of distributed suction through a finely perforated section of a symmetric airfoil on the spatial development of disturbances in the boundary layer are presented. It was found that distributed suction reduces by 10 times the intensity of natural disturbances of the boundary layer and by 20 times the intensity of artificial disturbances generated by an external acoustic field. A spectral analysis of disturbances showed that suction reduces the intensity of high-frequency fluctuations for both natural and forced disturbances. It was found that the distributed suction affects the average flow – when the suction is on, the separation of the boundary layer near the trailing edge of the wing is eliminated. It was found that distributed suction significantly affects the mean flow, up to eliminating the boundary-layer separation near the trailing edge of the wing.
Keywords
boundary layer, linear stability, Tollmien – Schlichting waves, distributed suction, disturbance spectrum
Funding
The work was partially completed (with distributed suction) within the framework of the program of fundamental scientific research of the state academies of Sciences for 2013–2020 (project AAAA17-117030610128-8) and with state support of scientific research conducted under the guidance of leading scientists in Russian universities, agreement No. 075-15-2019-1923
Control of the Laminar-Turbulent Transition on the Wing Profile by Distributed Suction through a Finely Perforated Surface
The material was received by the Editorial Board: 13.12.2019
Abstract The results of experimental investigations of the influence of distributed suction through a finely perforated section of a symmetric airfoil on the spatial development of disturbances in the boundary layer are presented. It was found that distributed suction reduces by 10 times the intensity of natural disturbances of the boundary layer and by 20 times the intensity of artificial disturbances generated by an external acoustic field. A spectral analysis of disturbances showed that suction reduces the intensity of high-frequency fluctuations for both natural and forced disturbances. It was found that the distributed suction affects the average flow – when the suction is on, the separation of the boundary layer near the trailing edge of the wing is eliminated. It was found that distributed suction significantly affects the mean flow, up to eliminating the boundary-layer separation near the trailing edge of the wing.
Keywords
boundary layer, linear stability, Tollmien – Schlichting waves, distributed suction, disturbance spectrum
Funding
The work was partially completed (with distributed suction) within the framework of the program of fundamental scientific research of the state academies of Sciences for 2013–2020 (project AAAA17-117030610128-8) and with state support of scientific research conducted under the guidance of leading scientists in Russian universities, agreement No. 075-15-2019-1923
Control of the Laminar-Turbulent Transition on the Wing Profile by Distributed Suction through a Finely Perforated Surface References: Grek G. R., Katasonov M. M., Kozlov V. V., Kornilov V. I., Kryukov A. V., Sadovskiy I. A. Control of the Laminar-Turbulent Transition on the Wing Profile by Distributed Suction through a Finely Perforated Surface . Siberian Journal of Physics . 2019, vol. 14, no. 4. P. 28–54. (in Russ.). DOI: 10.25205/2541-9447-2019-14-4-28-54