A vortex generator arrangement for an aircraft, comprising: - a surface portion (18, 19; 18, 51) facing and bounding a first region of space and adapted to constitute a flow surface for a flow present in operation in the first region of space, - a vortex generating element disposed in the first region of space, - an element support structure rigidly connected to the vortex generating element, - a mounting structure (3, 4, 15) to which the element support structure is mounted such that the element support structure and the vortex generating element together are rotatable with respect to the mounting structure (3, 4, 15) about a rotational axis between a first rotational position and a second rotational position, - a biasing means by means of which the vortex generating element is biased towards the second rotational position, - a retaining means (23, 30) adapted to retain the vortex generating element in the first rotational position against the biasing by the biasing means, and - a release means (24, 31) adapted to release the vortex generating element from the retaining means such that it is moved into the second rotational position by the biasing means, - wherein the rotational axis extends transversely with respect to the surface portion (18, 19; 18, 51), - wherein the vortex generating element is disposed completely in the first region of space in each rotational position thereof about the rotational axis, and - wherein the projection of the vortex generating element 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 and corresponding to the direction of the flow flowing over the flow surface during operation of the aircraft, characterized in that - the mounting structure (3, 4, 15) comprises a housing defining an interior space, which constitutes a second region of space and inside of which the biasing means, the retaining means, the release means and at least a part of the element support structure are located, wherein the surface portion (18, 19; 18, 51) is provided by an outer surface of the housing. - a surface portion (18, 19; 18, 51) facing and bounding a first region of space and adapted to constitute a flow surface for a flow present in operation in the first region of space, - a vortex generating element disposed in the first region of space, - an element support structure rigidly connected to the vortex generating element, - a mounting structure (3, 4, 15) to which the element support structure is mounted such that the element support structure and the vortex generating element together are rotatable with respect to the mounting structure (3, 4, 15) about a rotational axis between a first rotational position and a second rotational position, - a biasing means by means of which the vortex generating element is biased towards the second rotational position, - a retaining means (23, 30) adapted to retain the vortex generating element in the first rotational position against the biasing by the biasing means, and - a release means (24, 31) adapted to release the vortex generating element from the retaining means such that it is moved into the second rotational position by the biasing means, - wherein the rotational axis extends transversely with respect to the surface portion (18, 19; 18, 51), - wherein the vortex generating element is disposed completely in the first region of space in each rotational position thereof about the rotational axis, and - wherein the projection of the vortex generating element 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 and corresponding to the direction of the flow flowing over the flow surface during operation of the aircraft, - the mounting structure (3, 4, 15) comprises a housing defining an interior space, which constitutes a second region of space and inside of which the biasing means, the retaining means, the release means and at least a part of the element support structure are located, wherein the surface portion (18, 19; 18, 51) is provided by an outer surface of the housing.