Definition of Wingtip Devices Shape and Dimensions for a Subsonic Airliner
- Authors: Gueraiche D.1, Popov S.A.1, Ryzhov Y.A.1
-
Affiliations:
- Moscow Aviation Institute (National Research University)
- Issue: Vol 61, No 3 (2018)
- Pages: 331-339
- Section: Flight Vehicle Design
- URL: https://journals.rcsi.science/1068-7998/article/view/230574
- DOI: https://doi.org/10.3103/S1068799818030030
- ID: 230574
Cite item
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.
About the authors
D. Gueraiche
Moscow Aviation Institute (National Research University)
Email: flowmech@mail.ru
Russian Federation, Volokolamskoe sh. 4, Moscow, 125993
S. A. Popov
Moscow Aviation Institute (National Research University)
Author for correspondence.
Email: flowmech@mail.ru
Russian Federation, Volokolamskoe sh. 4, Moscow, 125993
Yu. A. Ryzhov
Moscow Aviation Institute (National Research University)
Email: flowmech@mail.ru
Russian Federation, Volokolamskoe sh. 4, Moscow, 125993