Abstract
The results of flow field numerical simulation on the typical wing-body prototype of the modern DLR-F4 airliner under sub- and transonic compressible air flow are presented. Using the DLR-F4 CAD model, the effect of the wingtip end plate area and of the cant angle of a typical Whitcomb winglet is studied. The dependencies of the model lift-to-drag ratio increment on the flat wingtip end plate relative area and on the cant angle of an airfoil Whitcomb winglet are obtained. The concept of an elliptic winglet with a variable cant angle that similar to the winglet used on Airbus A350 is studied. A technique is developed for solving the multi-parameter design optimization task for the Whitcomb winglet, taking the maximum lift-to-drag ratio of the wing as a criterion for optimization.
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Original Russian Text © D. Gueraiche, S.A. Popov, Yu.A. Ryzhov, 2018, published in Izvestiya Vysshikh Uchebnykh Zavedenii, Aviatsionnaya Tekhnika, 2018, No. 3, pp. 14–21
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Gueraiche, D., Popov, S.A. & Ryzhov, Y.A. Definition of Wingtip Devices Shape and Dimensions for a Subsonic Airliner. Russ. Aeronaut. 61, 331–339 (2018). https://doi.org/10.3103/S1068799818030030
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DOI: https://doi.org/10.3103/S1068799818030030