Novel wing profile for aircraft.

Abstract

Novel airfoil profile for aircraft, wherein the relocation of the greatest wing thickness to the rear wing area results in a new wing shape consisting of a convexly shaped, backward-sloping upper wing surface (1) and a lower wing surface (2), both of which are brought together in a pointed shape at the wing leading edge (3), wherein the straight part (4) of the lower wing surface (2) extends obliquely downwards to the rear, is continued in a rounded shape (5) in the area of ​​the greatest wing thickness and is joined upwards at the wing tip (6) with the upper wing surface (1).

Description

[0001] The invention relates to a novel airfoil profile for aircraft, which can also be used in rotor blades of helicopters and wind turbines.

[0002] Due to climate change, it is necessary to structurally modify aircraft wing profiles. To meet some of these requirements, it is known to improve wing profiles through gradual modifications.

[0003] Familiar airfoil profiles resemble elongated teardrops that taper towards their tips. This shape results in large frontal areas, which significantly reduces the thrust of aircraft. Furthermore, this also slows the airflow around the wingtips, resulting in suboptimal lift forces.

[0004] A novel airfoil profile results from the NL 932069 A, whose leading edge features a beak-shaped wingtip that transitions into a concave upper surface and a convex lower surface. Due to its concave shape, the upper surface contributes very little to lift. On the contrary, its height, which exceeds the wingtip towards the trailing edge, reduces lift. This is not compensated for by the convex lower surface, which, unlike conventional wings, has a steeper angle of attack.

[0005] The invention is based on the objective of creating a novel airfoil profile that increases the speed of aircraft, enhances their lift and improves their fuel consumption.

[0006] This problem is solved according to the invention by a novel wing profile for aircraft according to claim 1.

[0007] The advantages achieved with the invention lie in the fact that shifting the greatest wing thickness from the leading to the trailing edge creates a new airfoil profile. This allows the upper and lower surfaces of the wing to meet at the leading edge in a pointed shape, thus minimizing airflow resistance. This shape also enables the airflow to be divided into upper and lower airflows that surround the wing surfaces without turbulence or loss, thereby optimally increasing the wing's lift. The lower airflow is further compressed more strongly than with conventional airfoil profiles by the steep, rearward-sloping lower wing surface. Towards the wingtip, the high overpressure formed below the wing combines with the low pressure above the wing.This occurs very powerfully in the form of pressure equalization and, due to the rounded, upward-leading underside of the wing, provides a further pressure impulse in the direction of flight.

[0008] Thanks to performance improvements, aircraft equipped with these novel wing profiles can fly faster and higher with less fuel than previously possible. Used in helicopters and wind turbines as rotor blades, they significantly and sustainably increase efficiency.

[0009] An embodiment of the invention is shown in the drawing. It shows Fig. 1 Novel airfoil profile for aircraft.

Claims

[1] Novel airfoil profile for aircraft, wherein the relocation of the greatest wing thickness to the rear wing area results in a new wing shape consisting of a convexly shaped, backward-sloping upper wing surface (1) and a lower wing surface (2), both of which are brought together in a pointed shape at the wing leading edge (3), wherein the straight portion (4) of the lower wing surface (2) extends obliquely downwards to the rear, is continued in a rounded shape (5) in the area of ​​the greatest wing thickness and is joined upwards at the wing trailing edge (6) with the upper wing surface (1).

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