The present invention relates to a vortex generator arrangement for an aircraft (51), and to a flow control system and an aircraft comprising such vortex generator arrangement. The vortex generator arrangement comprises a surface portion (18, 19; 18, 51) facing a first region of space and adapted to constitute a flow surface, a vortex generating element (21) disposed in the first region of space, an element support structure (10) rigidly connected to the vortex generating element (21), a mounting structure (3, 4, 15) to which the element support structure (10) is mounted such that the element support structure (10) and the vortex generating element (21) together are rotatable with respect to the mounting structure (3, 4, 15) about a rotational axis (40) between a first rotational position and a second rotational position, a biasing means biasing the vortex generating element (21) towards the second rotational position, a retaining means adapted to retain the vortex generating element (21) in the first rotational position, and a release means adapted to release the vortex generating element (21) from the retaining means. The rotational axis (40) extends transversely with respect to the surface portion (18, 19; 18, 51). The vortex generating element (21) is disposed completely in the first region of space in each rotational position thereof about the rotational axis (40). The projection of the vortex generating element (21) onto a projection plane is smaller in the first rotational position than in the second rotational position, wherein the projection plane extends perpendicularly to a tangent plane of the surface portion (18, 19; 18, 51) at a reference point of the surface portion (18, 19; 18, 51) and to a predetermined direction parallel to the extension of the tangent plane.
A VORTEX GENERATOR ARRANGEMENT FOR AN AIRCRAFT
WIRBELGENERATORANORDNUNG FÜR EIN LUFTFAHRZEUG
DISPOSITIF DE GÉNÉRATION DE TOURBILLONS POUR UN AÉRONEF
2019-09-04
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge |