S. Helm, M. Haupt, B. Stickan, H. Bleecke

Previous work revealed that cross-sectional deformation of an aircraft wing at transonic speeds might have a considerable influence on shock prediction and, thus, on wave drag. CFD-CSM coupling based on standard FEM was, so far, not able to predict this camber deformation accurately over the whole chord, i.e. including leading edge and trailing edge devices. The objective of this work is to overcome this restriction through the use of an enhanced structural representation in the form of a multi-body model. The coupling of these models to CFD meshes is discussed. Finally, an improved representation of the cambering can be shown. Wings of commercial aircraft consist of a main structure fixed to the fuselage and equipped with different types of movable surfaces in order to manoeuvre the flying aircraft and to support its take-off and landing performance. The safe operation of these devices must be ensured. For this purpose, static multi-body simulations are used in an industrial environment. This work presents an advanced process which enables coupling of these multi-body models directly to high-fidelity CFD. Results are presented and assessed regarding design of wing and movable surfaces.

Deutscher Luft- und Raumfahrtkongress 2015, Rostock

Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn, 2016

Conference Paper

englisch

21,0 x 29,7 cm, 7 Seiten

urn:nbn:de:101:1-201602297602

CFD-CSM, manoeuvre loads

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29.02.2016