An flow body (2) comprises a curved suction skin (16) having a first perforation, a leading edge (18) and two skin sections extending therefrom, wherein each skin section has an outer end (20, 22) facing away from the leading edge (18), an interior suction duct (42) having a second perforation (44) and extending through an inside of the curved suction skin (16) in a distance from the leading edge (18), and two sidewall members (54, 56), connected to the outer ends (20, 22), wherein the sidewall members (54, 56) are made of a composite material. The suction skin (16) comprises a profiled contour shape, which determines a pressure distribution over at least one of the two skin sections when air flows over the curved suction skin (16), wherein the pressure distribution comprises a stagnation point, a suction peak and a subsequent local pressure maximum downstream of the suction peak, wherein the first perforation extends from a stagnation point on the suction skin (16) to the local pressure maximum. The air sucking fuselage component requires less material and is easier to manufacture due to a smaller extension of a required suction area having the first perforation.
Flow body, method for manufacturing a flow body and aircraft having such a flow body
Strömungskörper, Verfahren zur Herstellung eines Strömungskörpers und Flugzeug mit solch einem Strömungskörper
Corps d'écoulement, procédé de fabrication d'un corps d'écoulement et aéronef comprenant un tel corps d'écoulement
2020-07-22
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge |
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