CN218463864U

CN218463864U - V-shaped vortex generator for improving flow characteristics of eVTOL aircraft airfoil

Info

Publication number: CN218463864U
Application number: CN202222250774.2U
Authority: CN
Inventors: 董明; 王继明; 姚远; 杨万里; 党铁红
Original assignee: Shanghai Volant Aerotech Ltd
Current assignee: Shanghai Volant Aerotech Ltd
Priority date: 2022-08-26
Filing date: 2022-08-26
Publication date: 2023-02-10
Anticipated expiration: 2032-08-26

Abstract

The utility model discloses a V type vortex generator for improving eVTOL aircraft airfoil flow characteristic, including the water conservancy diversion piece, the water conservancy diversion piece is the thin slice structure, two the water conservancy diversion piece is distributed according to "V" type, forms "V" type water conservancy diversion piece right, "V" type water conservancy diversion piece is to being equipped with the multiunit to distribute according to the row and install in the airfoil disengagement zone, there is the contained angle with the incoming flow. The V-shaped vortex generator can effectively generate a double vortex queue, and the lift coefficient and the stall attack angle are increased; the V-shaped vortex generator can effectively improve the flow separation of the airfoil under a large attack angle, and reduce the aerodynamic noise and the structural vibration caused by the flow separation.

Description

V-shaped vortex generator for improving airfoil flow characteristics of eVTOL aircraft

Technical Field

The utility model relates to an aeronautical technical field, concretely relates to V type vortex generator for improving eVTOL aircraft airfoil flow characteristic.

Background

Electric vertical take-off and landing (eVTOL) aircraft applications involve a variety of scene modes, such as urban passenger transport, regional passenger transport, and the like. The eVTOL mainly has three configurations, namely a multi-rotor configuration, a composite wing configuration and a tilt wing configuration. The multi-rotor realizes the takeoff, landing and flat flight of the eVTOL by utilizing a plurality of propellers. The eVTOL mission profile typically involves interconversion between multi-rotor and fixed-wing, requiring the aircraft to have sufficient stall margin for the fixed-wing and transition phases. Due to the blocking of the motor arm and the propeller, the airflow energy of the upper airfoil surface of the wing is weakened, generally, as the attack angle increases, the fixed wing airfoil surface has a flow separation phenomenon at the trailing edge, and the separation area is further enlarged as the attack angle increases, so that the airplane enters stall if the separation area is not controlled. Therefore, the improvement of the low-speed characteristic of the electric vertical take-off and landing aircraft needs to improve the wing surface flow separation of the wing.

The airfoil flow separation means that airflow does not adhere to an object surface in certain areas of the airfoil, and the separation causes lift deviation from linearity, increased resistance and noise increase and structural vibration problems caused by the lift deviation. Further development and enlargement of the separation can cause the aircraft to stall. Stall refers to the flight condition that corresponds to when the aircraft reaches the maximum available lift coefficient. The stall condition of an aircraft is typically defined in terms of stall angle of attack or stall speed. In a stall condition, non-commanded roll, pitch, or yaw motions of the aircraft may occur. Thus, sufficient margin must be ensured in flight to prevent the aircraft from entering stall.

The vortex generator is a device for improving the flow separation of the boundary layer, and the principle of the vortex generator is to inject high-energy fluid outside the boundary layer into low-energy fluid inside the boundary layer, so that the boundary layer obtains high external energy, thereby improving the anti-separation capability of the boundary layer. However, the conventional vortex generator has a complex structure and correspondingly increases the weight of the system, and the electric vertical take-off and landing aircraft has high requirements on the weight.

SUMMERY OF THE UTILITY MODEL

The utility model aims at providing a V type vortex generator for improving eVTOL aircraft airfoil flow characteristics to solve the problem mentioned in the background art. In order to achieve the above object, the utility model provides a following technical scheme: the V-shaped vortex generator for improving the flow characteristics of the airfoil of the eVTOL aircraft comprises guide vanes, wherein the guide vanes are of a sheet structure, the two guide vanes are distributed according to a V shape to form a V-shaped guide vane pair, the V-shaped guide vane pair is provided with a plurality of groups and is arranged in an airfoil separation area in a row distribution mode, and an included angle is formed between the V-shaped guide vane pair and an incoming flow.

Preferably, the distance between two said pairs of "V" shaped guide vanes is larger than the range of the vortex generated by each pair of "V" shaped guide vanes.

Preferably, the plane shape of the guide vane is a rectangular, trapezoidal or arc structure.

Preferably, the height of the pair of "V" shaped guide vanes exceeds the boundary layer height.

The utility model discloses a technological effect and advantage: the V-shaped vortex generator can effectively generate a double vortex queue, and the lift coefficient and the stall attack angle are increased; the V-shaped vortex generator can effectively improve flow separation of the airfoil under a large attack angle, and reduce aerodynamic noise and structural vibration caused by flow separation.

Drawings

FIG. 1 is a top view of the installation position of the present invention;

FIG. 2 is a schematic view of the arrangement position of the present invention;

FIG. 3 is a side view of the installation position of the present invention;

fig. 4 is a schematic layout diagram of the present invention;

FIG. 5 is a schematic diagram of a twin-tailed vortex of the present invention;

fig. 6 is a schematic view of the flow deflector of the present invention having a rectangular planar shape;

fig. 7 is a schematic view of the flow deflector of the present invention with a trapezoidal planar shape;

fig. 8 is a schematic view of the flow deflector with an arc-shaped planar shape according to the present invention.

In the figure: 1-wing, 2-propeller, 3-fuselage, 4-V type vortex generator, 5-motor arm, 6- 'V' type guide vane pair.

Detailed Description

In order to make the technical means, the creative features, the objectives and the functions of the present invention easily understood and appreciated, the present invention will be further described with reference to the specific drawings, and in the description of the present invention, unless otherwise specified or limited, the terms "mounted," connected "and" connected "should be understood broadly, and for example, the terms" fixed connection, "detachable connection," integral connection, mechanical connection, and electrical connection may be used; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements.

Examples

As shown in fig. 1, the installation of the V-shaped vortex generator on the evtol aircraft is schematically shown, and due to the interference of the fuselage 3, especially the close coupling of the propeller 2 and the motor arm 5 with the wing 1, the wing airfoil is separated in advance compared with the state of a clean wing. As shown in fig. 2-4, the V-shaped vortex generator 4 includes flow deflectors, the flow deflectors are in a sheet structure, two flow deflectors are distributed in a V shape to form a V-shaped flow deflector pair 6, the V-shaped flow deflector pair 6 is provided with a plurality of groups, and is arranged at the upstream of the wing upper airfoil surface separation area in a row distribution, and forms an angle with the incoming flow, the height generally exceeds the height of the boundary layer, and the wake vortex generated under a larger attack angle enables the wing surface separation flow of the wing 1 to be attached again, so as to delay the occurrence of separation.

The distance between each pair of V-shaped guide vane pairs 6 and other pairs is proper, and the distance is larger than the vortex range generated by each V-shaped guide vane pair 6, so that the mutual interference of the vortices is avoided, and the adverse effect is avoided.

The V-vortex generator 4 generates double wake vortices as shown in fig. 5, and each pair of "V" type guide vane pairs 6 generates vortices with opposite rotation directions. The induced velocity directions of the pairs of V-shaped guide vanes 6 are consistent from pair to pair and at the symmetry plane of each pair, and therefore mutually strengthen. The high-speed rotating flow of the high-speed rotating flow also generates corresponding downward washing flow while injecting the energy of the boundary layer, so that the downstream separated flow is closer to the wall surface and further adheres to the wall surface, and the lift force and the stall attack angle are improved. Therefore, the position thereof is not limited to that shown in fig. 1. Its chordwise location is generally disposed before the separation zone, but need not be near the leading edge of the wing; the unfolding position of the wing-shaped aircraft depends on the separation position of the wing surface, is related to the separation characteristic of the wing surface of the wing, and is different from different wings or different airplanes.

The plane shape of the guide vane of the V-shaped vortex generator 4 is shown in fig. 6 to 8. Generally rectangular, trapezoidal or arcuate, but not limited to the above, may be a combination of the above solutions, the shape of which is designed to more efficiently and stably generate vortices against the generation and development of the flow separation area of the airfoil.

Finally, it should be noted that: although the present invention has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that modifications and variations can be made in the embodiments or in part of the technical features of the embodiments without departing from the spirit and the scope of the invention.

Claims

1. V-shaped vortex generator for improving the flow characteristics of an eVTOL aircraft airfoil, comprising a guide vane, characterized in that: the flow deflectors are of a thin-sheet structure, the two flow deflectors are distributed according to a V shape to form a V-shaped flow deflector pair, the V-shaped flow deflector pair is provided with a plurality of groups and is arranged in the airfoil surface separation area according to the row distribution, and an included angle is formed between the V-shaped flow deflectors and the incoming flow.

2. The V-vortex generator for improving the flow characteristics of an eVTOL aircraft airfoil according to claim 1, wherein: the distance between two said pairs of "V" shaped guide vanes is larger than the range of the vortex generated by each pair of "V" shaped guide vanes.

3. The V-vortex generator for improving the flow characteristics of an eVTOL aircraft airfoil according to claim 1, wherein: the plane shape of the flow deflector is a rectangular, trapezoidal or arc structure.

4. The V-vortex generator for improving the flow characteristics of an eVTOL aircraft airfoil according to claim 1, wherein: the height of the V-shaped guide vane pair exceeds the height of the boundary layer.