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
STRÖMUNGSKÖRPER FÜR EIN FLUGZEUG MIT MASSIVER EINTRITTSKANTENKOMPONENTE
ÉLÉMENT AÉRODYNAMIQUE POUR UN AÉRONEF COMPORTANT UN COMPOSANT DE BORD DE FUITE PLEIN
2022-04-06
Patent
Elektronische Ressource
Englisch
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