An aircraft structure component (1) for laminar flow, the aircraft structure component (1) having an outer skin (3) with an aerodynamic surface (5), wherein the aerodynamic surface (5) has a leading edge portion (7) and a downstream portion (11) adjacently downstream from the leading edge portion (7), and wherein the downstream portion (11) of the aerodynamic surface (5) comprises a paint layer (13) that is not present in the leading edge portion (7), so that an edge line (15) is formed between the leading edge portion (7) and the downstream portion (11) by the beginning paint layer (13). The object, to provide an aircraft structure component that allows for a reduced aerodynamic drag, is achieved in that the edge line (15) has a ramp-shaped cross section (17), wherein the thickness of the paint layer (13) increases from a starting point (19) over a predetermined ramp length (21) to a saturation point (23) where the full thickness (25) of the paint layer (13) is reached.
AN AIRCRAFT STRUCTURE COMPONENT FOR LAMINAR FLOW
FLUGZEUGSTRUKTURBAUTEIL FÜR LAMINARSTRÖMUNG
COMPOSANT DE STRUCTURE D'AÉRONEF POUR UN ÉCOULEMENT LAMINAIRE
2021-07-28
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge |