A flow body for an aircraft, in particular for a wing leading edge device, is proposed, the flow body having a curved front skin having a leading edge and at least one trailing-edge component coupled with at least one spanwise edge of the front skin, wherein the trailing-edge component comprises a constant cross-sectional profile that tapers in a chordwise direction to form two spanwise flow surfaces that end in a trailing edge, and wherein the trailing-edge component is designed for providing a flush transition between the front skin and at least one of the two spanwise flow surfaces.
FLOW BODY FOR AN AIRCRAFT HAVING A SOLID TRAILING-EDGE COMPONENT
2022-04-21
Patent
Elektronische Ressource
Englisch
FLOW BODY FOR AN AIRCRAFT HAVING A SOLID TRAILING-EDGE COMPONENT
Europäisches Patentamt | 2021
|Flow body for an aircraft having a solid trailing-edge component
Europäisches Patentamt | 2024
|FLOW BODY FOR AN AIRCRAFT HAVING A SOLID TRAILING-EDGE COMPONENT
Europäisches Patentamt | 2020
|FLOW BODY FOR AN AIRCRAFT HAVING A SOLID TRAILING-EDGE COMPONENT
Europäisches Patentamt | 2022
|