Propeller-driven aircraft wing and propeller-driven aircraft

Abstract

The invention belongs to the field of aircraft aerodynamic design, and particularly relates to a propeller-driven aircraft wing and a propeller-driven aircraft. In a first aspect, for a propeller-driven aircraft wing, a droop is provided at a leading edge portion of the wing at its wash-up zone; in the second aspect, the aircraft with the propellers rotating in the same direction comprises wings on the left side and the right side, and drooping parts of front edge parts of the wings on the left side and the right side are asymmetrically distributed. According to the propeller-driven aircraft wing and the propeller-driven aircraft, a left wing flow field and a right wing flow field generated by homodromous rotation of propellers on two sides are asymmetric; the leading edge of the wing within a certain range on one side of the propeller-driven aircraft washing area is drooped linearly, so that the standing point line of the leading edge of the wing moves downwards, the surface speeds ofthe leading edge wing and the nacelle are reduced, the whole aircraft resistance of the aircraft is reduced, the lift-drag ratio of the propeller-driven aircraft is increased, and the performance ofthe propeller-driven aircraft is improved.

Description

technical field [0001] The application belongs to the field of aircraft aerodynamic design, in particular to a propeller aircraft wing and a propeller aircraft. Background technique [0002] For propeller aircraft, especially those with co-rotating propellers, the layout of the engine nacelle installed under the wings will cause greater interference between the nacelle and the wings, forming an important source of resistance for the aircraft; The helical slipstream changes the original flow state of the wing, and also changes the distribution of the spanwise circulation of the wing. The part of the wing covered by the slipstream bears higher dynamic pressure than the adjacent part of the wing, resulting in greater In the actual flow, the lift of the wing is not only affected by the dynamic pressure increase in the slipstream, but also by the slipstream rotation effect. [0003] Also, the rotational effect changes the local angle of attack on the part of the wing covered by ...

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