V.M. Singh, P. Scholz

This contribution presents the investigation of a passive method of boundary layer separation control on a swept and tapered vertical tail plane with a deflected rudder. The primary objective was the increase of the total side force coefficient. For that, an array of co-rotating vane vortex generators was placed close to the rudder knee to maintain an attached flow, which consequently led to an increase of the side force coefficient. The second objective was a parameter sensitivity study, which covered a large scope of different vane vortex generator parameters: size, shape, angle of attack, position and separation. Experiments were performed in a low-speed wind tunnel. The results show the ability of vane vortex generators to increase the side force coefficient for a large range of yaw angles. The maximal increase of side force coefficient was about 14 %. However, the influence of the vane vortex generators on the stall of the vertical tail plane was limited. Nevertheless, in a range of yaw angles, an increase of the lift to drag ratio of about 30 % was obtained. The effect was found to be sensitive for the angle of attack, chordwise position, size and geometry of a vortex generator, whereas parameters such as spanwise extension and separation were less sensitive to parameter change.

Deutscher Luft- und Raumfahrtkongress 2017, München

Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn, 2018

Conference Paper

englisch

21,0 x 29,7 cm, 9 Seiten

urn:nbn:de:101:1-201803024572

Flugzeugaerodynamik, Strömungskontrolle

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02.03.2018