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The scope of the paper is to present the results of a RANS based aerodynamic high-lift design for a natural laminar flow wing with negative sweep. The chosen high-lift system consists of a Krueger leading edge flap with shielding function and a fixed-vane trailing edge flap. The design was first optimized in two main wing sections and then verified by 3D RANS siumlations of a wing-body model. Finally, engines were added to the geometric model in order to estimate the high-lift performance of the landing configuration. With a maximum lift coefficient of CL = 2:85 for the wing-body model with engine, the target from the preliminary aircraft design was reached. Further potential for improvement was found in the optimization strategy and the shape of the fuselage-wing junction.
Deutscher Luft- und Raumfahrtkongress 2017, München
Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn, 2018
21,6 x 27,9 cm, 12 Seiten
Stichworte zum Inhalt:
TuLam, Natural Laminar Flow