Low speed airfoil design for aerodynamic improved performance of UAVs
AssigneeThe Boeing Company
InventorsBradley M. Hopping, Timothy M. Garrett
Life of this patent
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Abstract
An airfoil configured for low speed performance in an unmanned aerial vehicle includes an upper surface having an upper surface portion with a top local surface angle magnitude of less than 5 degrees at a subsection of a chord and a lower surface having a lower surface portion with a bottom local surface angle magnitude of less than 5 degrees at the subsection of the chord. The chord is defined by a line starting at a leading edge of the airfoil and extending to a trailing edge of the airfoil.
Claims17
An airfoil for an unmanned aerial vehicle, the airfoil comprising:
- an upper surface having an upper surface portion with a top local surface angle magnitude of less than 5 degrees at a subsection of a chord, wherein the chord is defined by a line starting at a leading edge of the airfoil and extending to a trailing edge of the airfoil;
- a lower surface having a lower surface portion with a bottom local surface angle magnitude of less than 5 degrees at the subsection of the chord;
- and
- a maximum thickness defined between the upper surface and the lower surface, wherein the maximum thickness extends a length from substantially 20% to substantially 40% of the chord.
An unmanned aerial vehicle (UAV) comprising:
- a fuselage;
- a propulsion unit mechanically coupled to the fuselage;
- and
- an airfoil coupled to the fuselage, the airfoil including:
- an upper surface having an upper surface portion having a top local surface angle magnitude less than 5 degrees at a subsection of a chard, wherein the chord is defined by a line starting at a leading edge of the airfoil and extending to a trailing edge of the airfoil, a lower surface having a lower surface portion having a bottom local surface angle magnitude less than 5 degrees at the subsection of the chord, and a maximum thickness defined between the upper surface and the lower surface, wherein the maximum thickness extends a length from substantially 20% to substantially 40% of the chord.
A method of assembling an unmanned aerial vehicle, the method comprising:
- providing a fuselage;
- attaching a propulsion unit to the fuselage;
- and
- attaching an airfoil to the fuselage, the airfoil having an upper surface that includes an upper surface portion having a top local surface angle magnitude less than 5 degrees at a subsection of a chord, wherein the chord is defined by a line starting at a leading edge of the airfoil and extending to a trailing edge of the airfoil, a lower surface that includes a lower surface portion having a bottom local surface angle magnitude less than 5 degrees at the subsection of the chord, and a maximum thickness defined between the upper surface and the lower surface, wherein the maximum thickness extends a length from substantially 20% to substantially 40% of the chord.
Dependencies are inferred from the claim text.