An unmanned aerial vehicle (UAV) (100) which includes a fuselage (102), a propulsion unit (104) mechanically coupled to the fuselage (102); and an airfoil (106) coupled to the fuselage (102). The airfoil (106) includes an upper surface (120) having an upper surface portion (164) having a top local surface angle magnitude less than 5 degrees at a subsection (168) of a chord (128). The chord (128) is defined by a line starting at a leading edge (124) of the airfoil (106) and extending to a trailing edge (126) of the airfoil (106). The airfoil (106) includes a lower surface (122) having a lower surface portion (166) with a bottom local surface angle magnitude of less than 5 degrees at the subsection of the chord. The airfoil (106) is configured to store fuel tank (146).
LOW SPEED AIRFOIL DESIGN FOR AERODYNAMIC IMPROVED PERFORMANCE OF UAVS
TRAGFLÄCHENPROFIL FÜR NIEDRIGE GESCHWINDIGKEIT FÜR VERBESSERTE AERODYNAMISCHE LEISTUNG VON UAVS
CONCEPTION AÉRODYNAMIQUE À FAIBLE VITESSE POUR DE MEILLEURES PERFORMANCES AÉRODYNAMIQUES D'UAV
2020-09-09
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |
LOW SPEED AIRFOIL DESIGN FOR AERODYNAMIC IMPROVED PERFORMANCE OF UAVS
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