CPC B64C 9/24 (2013.01) [B64D 15/14 (2013.01)] | 14 Claims |
1. A flow body for an aircraft, comprising a stiffening structure and a flow surface at least partially enclosing the stiffening structure, the flow surface having a leading edge and a trailing edge at a distance to each other in a chordwise direction, and a solid trailing edge element, the flow body further comprising:
a first heating device attached to or integrated into the flow surface in a first chordwise section,
a second heating device attached to or integrated into the flow surface in a second chordwise section,
wherein the first chordwise section and the second chordwise section are distanced from each other,
wherein the first chordwise section is closer to the leading edge than the second chordwise section,
wherein at least the second heating device comprises an electric heater, and
wherein the second heating device extends to a position directly in front of the solid trailing edge element.
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