Abstract
The results of numerical investigation of a simplified model of the civil aircraft layout in the landing regime are presented. Numerical simulation is performed within the framework of the Reynolds equations. The aerodynamic characteristics of the model are studied in the case in which the flow is controlled by means of mounting strakes (vortex generators) on the nacelle and the fuselage. It is shown that mounting simultaneously the two strakes leads to a considerable increase in the maximum lift of the layout, while in the case in which only one fence is mounted on either the nacelle or the fuselage it increases only slightly.
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Acknowledgements
The authors wish to thank S.I. Skomorokhov for assistance and discussion of the results of the calculations.
The study was carried out with the financial support of the Ministry of Science and Education of the Russian Federation (project identifier RFMEFI62817X0007).
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Russian Text © The Author(s), 2019, published in Izvestiya Rossiiskoi Akademii Nauk, Mekhanika Zhidkosti i Gaza, 2019, No. 1, pp. 78–85.
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Voevodin, A.V., Soudakov, V.G. Control of Flow Past a Model Aircraft in the Landing Configuration Using Aerodynamic Strakes. Fluid Dyn 54, 77–84 (2019). https://doi.org/10.1134/S0015462819010166
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DOI: https://doi.org/10.1134/S0015462819010166