K.C. Huber, A. Schütte, M. Rein, T. Löser

Extensive experimental and numerical investigations on a highly swept generic unmanned combat aerial vehicle (UCAV) configuration of lambda type with a variable leading edge contour have been conducted. Within these investigations it was shown that the flow field is dominated by complex vortex systems including vortex-to-vortex and vortex-to-boundary layer interactions. The vortex dominated flow field has a strong nonlinear influence on the aerodynamic behavior of the configuration. Hence, the controllability aspect is demanding and poses a real challenge in the design of this kind of configuration. Especially the dimensioning of the control surfaces for the lateral- and longitudinal stability aspects of tailless configurations of low aspect ratio and high leading edge sweep poses a challenging task, which is not yet solved. The present paper reviews the experimental aspects of the investigations. In order to understand the problem of lacking lateral- and longitudinal stability for these kind of configuration, experiments in the subsonic and transonic flow regime have been conducted for the SACCON configuration, which has a leading edge sweep of 53° in order to assess the control surface effectiveness of conventional trailing edge control devices. These investigations were undertaken as part of the internal DLR projects FaUSST and Mephisto.

Deutscher Luft- und Raumfahrtkongress 2015, Rostock

Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn, 2015

Conference Paper

englisch

21,0 x 29,7 cm, 11 Seiten

urn:nbn:de:101:1-20151109475

experiment, vortical flow

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06.11.2015