The present invention relates to an airfoil comprising a leading edge flap (210) providing a rigid leading edge surface profile contour (212); a central lifting section (220) aft of the rigid leading edge flap (210); a bottom side (208) comprising a lower surface contour section (232) formed at least by a lower surface section (228) of the rigid leading edge surface profile contour (212) and by a bottom surface (224) of the central lifting section (220); and a top side (206) comprising an upper surface contour section (234) formed at least by an upper surface section (230) of the rigid leading edge surface profile contour (212) and by a top surface (222) of the central lifting section (220). The rigid leading edge surface profile contour (212) is adapted to the central lifting section (220) such that at a first leading edge flap angle, the lower surface contour section (232) exhibits C1- and/or C2-continuity; and at a second leading edge flap angle, the upper surface contour section (234) exhibits C1- and/or C2-continuity. The present invention also relates to a lifting structure (W), such as a wing, comprising such an airfoil (200), and to a sailplane comprising such an airfoil (200).
DOUBLE FLAP LAMINAR AIRFOIL
LAMINARE DOPPELKLAPPENFLÜGELSCHAUFEL
PROFIL AÉRODYNAMIQUE LAMINAIRE À DOUBLE VOLET
2024-10-16
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |
NTRS | 2005
|Springer Verlag | 2017
|Wind-tunnel investigation of NACA 23012 airfoil with 0.30-airfoil-chord double slotted flap
Engineering Index Backfile | 1943
|Airfoil fitted with slotted flap
Engineering Index Backfile | 1936
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