WO2023124378A1

WO2023124378A1 - Propeller and aircraft

Info

Publication number: WO2023124378A1
Application number: PCT/CN2022/124711
Authority: WO
Inventors: 赵龙智; 郜奥林; 刘璐; 陆宏伟; 续立军; 邱一可; 吴振凯; 李桂华; 刘金来; 马聪; 刘宝俊; 高焓
Original assignee: 北京三快在线科技有限公司
Priority date: 2021-12-29
Filing date: 2022-10-11
Publication date: 2023-07-06
Also published as: CN116409458A

Abstract

A propeller and an aircraft. The propeller comprises a propeller blade (1) and a spoiler portion (2). At least part of the spoiler portion (2) protrudes out of a suction surface of the propeller blade (1), and the spoiler portion (2) extends in a spanwise direction of the propeller blade (1).

Description

propeller and aircraft

This application claims the priority of the Chinese patent application with the application number 202111633174.8 and the application name "A Propeller and Aircraft" filed on December 29, 2021, the entire contents of which are incorporated in this application by reference.

technical field

The present application relates to the technical field of aircraft, in particular to a propeller and an aircraft.

Background technique

The aircraft is equipped with a propeller, and the flight of the aircraft is realized through the disturbance of the airflow by the propeller. Since the aircraft has functions such as shooting and transporting materials, it is widely used in many industries such as surveying and mapping, logistics, and distribution.

Contents of the invention

The application provides a propeller and an aircraft, and the technical scheme is as follows.

The first aspect of the present application provides a propeller, which includes: a blade and a spoiler, at least part of which protrudes from the suction surface of the blade; wherein the spoiler extends along the span direction of the blade.

In this application, the spoiler extending along the spanwise direction of the blade is provided so that the airflow in the laminar flow region changes to turbulent flow in advance, that is, when the flow velocity of the airflow is relatively high, the laminar flow is transformed into turbulent flow, so that the flow velocity of turbulent flow increases, thereby making The airflow in the turbulent area can leave the surface of the blade faster, thereby reducing the collision area between the airflow in the turbulent area and the surface of the blade, so as to reduce noise.

In a possible design, along the chord direction of the blade, the blade also includes a leading edge and a trailing edge oppositely arranged, the vertical distance between the leading edge and the trailing edge is the chord length c of the blade, and the spoiler The distance L1 between the centerline and the leading edge satisfies: 0.05c≤L1≤0.6c.

In a possible design, along the direction of the chord length of the blade, the blade also includes a leading edge and a trailing edge oppositely arranged, the vertical distance between the leading edge and the trailing edge is the chord length c of the blade, and the operating environment of the propeller The Reynolds number is Re, and the height of the spoiler protruding from the suction surface is h, satisfying: h=kc/Re ^0.2 ; wherein, the proportional coefficient k satisfies: 0.01≤k≤0.2.

In a possible design, along the chord direction of the blade, the blade also includes a leading edge and a trailing edge oppositely arranged, the vertical distance between the leading edge and the trailing edge is the chord length c of the blade, and the spoiler The width L2 satisfies: 0.05c≤L2≤0.5c.

In a possible design, along the chord direction of the blade, the spoiler includes a first side wall and a second side wall oppositely arranged, at least part of the first side wall is sawtooth-shaped, and/or, the second At least a portion of the sidewall is serrated.

In a possible design, the spoiler includes a first side and a second side, and a plurality of first sides and a plurality of second sides are arranged at intervals and connected with each other to form a zigzag first side wall and/or a second side wall. Two side walls; the angle α between the first side and the second side satisfies: 10°<α<120°.

In a possible design, along the thickness direction of the blade, the blade includes a top surface and a bottom surface oppositely arranged, both the top surface and the bottom surface are suction surfaces, and the spoiler is arranged on the top surface, or the spoiler is arranged on the top surface face and bottom.

In a possible design, along the span direction of the blade, the spoiler runs through the blade, or the spoiler covers a part of the blade.

In a possible design, there are one or more spoilers; multiple spoilers are arranged at intervals or continuously.

In a possible design, the spoiler is integrally formed or fixedly connected to the paddle.

The second aspect of the present application provides an aircraft, the aircraft includes a body and a propeller installed on the body, and the propeller is the propeller described in any one of the above.

In this application, the propeller is provided with a spoiler extending along the span of the blade to increase the turbulent flow velocity, so that the area where the noise is generated on the surface of the blade is reduced, thereby reducing the noise generated during the working process of the propeller, thereby improving the use of the aircraft Performance, at the same time, can improve the concealment of the aircraft, thereby improving the application scenarios of the aircraft.

It is to be understood that both the foregoing general description and the following detailed description are exemplary only and are not restrictive of the application.

Description of drawings

Fig. 1 is a partial structural schematic diagram of a propeller provided by the present application;

Fig. 2 is a structural schematic diagram of a spoiler provided by the present application;

Fig. 3 is a schematic structural diagram of a spoiler provided by the present application;

FIG. 4 is a schematic diagram of a partial structure of a spoiler provided by the present application after the blade is installed.

Reference signs:

1 - paddle;

11-leading edge; 12-trailing edge;

2 - spoiler;

21 - first side wall; 22 - second side wall; 23 - first side; 24 - second side.

The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments consistent with the application and together with the description serve to explain the principles of the application.

Detailed ways

In order to better understand the technical solutions of the present application, the embodiments of the present application will be described in detail below in conjunction with the accompanying drawings.

It should be clear that the described embodiments are only some of the embodiments of the present application, not all of the embodiments. Based on the embodiments in this application, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of this application.

Terms used in the embodiments of the present application are only for the purpose of describing specific embodiments, and are not intended to limit the present application. The singular forms "a", "said" and "the" used in the embodiments of this application and the appended claims are also intended to include plural forms unless the context clearly indicates otherwise.

It should be understood that the term "and/or" used herein is only an association relationship describing associated objects, which means that there may be three relationships, for example, A and/or B, which may mean that A exists alone, and A and B exist simultaneously. B, there are three situations of B alone. In addition, the character "/" in this article generally indicates that the contextual objects are an "or" relationship.

It should be noted that the orientation words such as "up", "down", "left", and "right" described in the embodiments of the present application are described from the angles shown in the drawings, and should not be interpreted as limiting the implementation of the present application. Example limitations. Furthermore, in this context, it also needs to be understood that when it is mentioned that an element is connected "on" or "under" another element, it can not only be directly connected "on" or "under" another element, but can also To be indirectly connected "on" or "under" another element through an intervening element.

With the continuous development of aircraft technology, the application of aircraft in various industries is becoming more and more extensive. Wherein, the aircraft is provided with a propeller, and when the propeller rotates, the propeller disturbs the air flow, so that the flight of the aircraft can be realized. During the flight of the aircraft, because the propeller disturbs the airflow, it will cause collision between the airflow and the airflow and the propeller to generate noise, thereby reducing the performance of the aircraft.

Among them, the noise generated above belongs to aerodynamic noise, and aerodynamic noise is mainly divided into broadband noise and harmonic noise. Based on the different designs of propellers and different working conditions where propellers are required to be used, the relative proportions of these two kinds of noise may also be different. When reducing noise for propellers, it is often chosen to change the thickness distribution, chord length distribution, and torsional distribution of the blades to reduce harmonic noise. However, there is a lack of widely applicable noise reduction methods for broadband noise.

The embodiment of the present application provides a propeller, as shown in Figure 1, the propeller includes: a blade 1; a spoiler 2, at least part of the spoiler 2 protrudes from the suction surface of the blade 1; wherein, the spoiler 2 extends along the length direction of the blade 1.

Wherein, the length direction of the blade 1 is the span direction of the blade 1 , and the span direction is the direction indicated by r or R in FIG. 1 . Exemplarily, for a spoiler 2, the spoiler 2 extends along the span direction of the blade 1, which may refer to: the projected length of the spoiler 2 in the span direction is greater than that of the spoiler 2 in the The projected length in the direction of the chord length, the direction of the chord length is the direction shown in c in Figure 1.

If the blade 1 does not include the turbulence part 2, the airflow will be stirred during the operation of the propeller, so that the laminar flow changes into a turbulent flow. Due to the chaotic direction of the airflow in the turbulent flow area, the collision between the airflow and the airflow will occur, and part of the airflow will collide with the airflow. The surface of the paddle 1 collides, thereby generating a large noise. The energy of the airflow decreases due to the collision of the airflow, so that the flow velocity of the airflow decreases, that is, along the chord direction of the blade 1 , the flow velocity of the airflow at the front end of the blade 1 is greater than the flow velocity of the airflow at the rear end of the blade 1 . Just because the flow velocity of the airflow at the front end of the blade 1 is greater than the flow velocity of the airflow at the rear end of the blade 1, a reverse pressure gradient will be formed on the blade 1, which will lead to the generation and development of laminar separation bubbles at the front end of the blade 1, thereby resulting in loud noise.

However, in the embodiment of the present application, the spoiler 2 extending along the span direction of the blade 1 is provided. During the operation of the blade 1 , the spoiler 2 will further disturb the airflow in addition to the blade 1 stirring the airflow. The spoiler 2 is equivalent to a forward step, which can intervene in the generation and development of the above-mentioned laminar flow separation bubbles, so that the airflow in the laminar flow area changes to turbulent flow in advance, that is, the laminar flow is transformed into turbulent flow when the airflow velocity is relatively high, In other words, the spoiler 2 can transform laminar flow into turbulent flow.

Therefore, the flow velocity of the turbulent flow is increased, and the turbulent kinetic energy is improved, so that the airflow in the turbulent flow area can leave the surface of the blade 1 faster, and the thickness of the turbulent boundary layer is reduced, thereby reducing the air flow in the turbulent flow area and the blade 1. Surface collision area to reduce noise.

The propeller provided by the embodiment of the present application can at least reduce bandwidth noise, and can also reduce bandwidth noise and harmonic noise, thereby reducing aerodynamic noise. Exemplarily, after testing, the propeller provided by the embodiment of the present application can reduce noise by about 2dBA (decibels adjusted, adjusted decibels). This noise reduction method is simple, has high feasibility, and is suitable for various engineering applications. Moreover, this noise reduction method has little impact on the aerodynamic characteristics of the blade 1 and will not affect the normal use of the propeller.

Exemplarily, as shown in Fig. 1 and Fig. 4, along the chord direction of the blade 1, the blade 1 also includes a leading edge 11 and a trailing edge 12 oppositely arranged, and the vertical distance between the leading edge 11 and the trailing edge 12 is is the chord length c of the blade 1 , and the distance L1 between the center line of the spoiler 2 and the leading edge 11 satisfies: 0.05c≤L1≤0.6c. For example, the distance L1 satisfies 0.1c≦L1≦0.5c.

In this embodiment, if L1 is too small, such as less than 0.05c, the impact of the air flow on the spoiler 2 during the operation of the blade 1 is too large, and damage to the spoiler 2 is likely to occur; if L1 is too large, If it is greater than 0.6c, the spoiler 2 is located in the turbulent area or behind the turbulent area, and the noise reduction effect of the spoiler 2 is low or even ineffective. Therefore, 0.05c≦L1≦0.6c can prolong the service life of the spoiler 2 and improve the noise reduction effect of the spoiler 2 at the same time.

Along the running direction of the blade 1 , that is, the direction indicated by the arrow on the left side of the blade 1 in FIG. 1 , the front end of the blade 1 is a leading edge 11 , and the rear end of the blade 1 is a trailing edge 12 . If the leading edge 11 and the trailing edge 12 of the blade 1 are parallel, then the chord length c of the blade 1 on the unit length is a constant value, if the shape variation rules of the leading edge 11 and the trailing edge 12 of the blade 1 are different, The chord length c of the blade 1 per unit length is constantly changing, therefore, the distance L1 between the center line of the spoiler 2 and the leading edge 11 can be a constant value, or can be constantly changing.

Exemplarily, as shown in Figures 2 and 3, along the chord direction of the blade 1, the Reynolds number of the propeller operating environment is Re, and the height of the spoiler 2 protruding from the top surface is h, satisfying: h=kc/Re ^0.2 ; Wherein, the proportional coefficient k satisfies: 0.01≤k≤0.2. Wherein, the top surface belongs to the suction surface, then the height of the spoiler 2 protruding from the top surface can be considered as the height of the spoiler 2 protruding from the suction surface, and the height of the spoiler 2 protruding from the suction surface is shown as h is represented as H in FIG. 2 , that is, H satisfies: H=kc/Re ^0.2 .

In this embodiment, if h is too small, such as less than 0.01, the air flow in the turbulent region that can be disturbed by the spoiler 2 is too small, resulting in low noise reduction effect of the spoiler 2; if h is too large, such as greater than 0.2 , the spoiler 2 is higher than the turbulent flow region to interfere with the airflow in the laminar flow region and generate greater noise. Therefore, h=kc/Re ^0.2 and 0.01≦k≦0.2, while ensuring the normal operation of the spoiler 2 , the working effect of the spoiler 2 is improved.

Among them, if the leading edge 11 and the trailing edge 12 of the blade 1 are parallel, then along the span direction of the blade 1, the chord length c per unit length is a constant value, if the leading edge 11 and the trailing edge 12 of the blade 1 The shape change rules of the turbulence are different, and the chord length c per unit length is constantly changing. Therefore, the height h of the protruding top surface of the spoiler 2 per unit length can be a constant value, or it can be constantly changing.

Exemplarily, as shown in FIGS. 2 to 4 , the width L2 of the spoiler 2 satisfies: 0.05c≤L2≤0.5c.

In this embodiment, if L2<0.05c, the width of the spoiler 2 is too small, resulting in poor strength of the spoiler 2. During the working process of the propeller, the spoiler 2 is easily deformed under the action of the airflow. The spoiler 2 is ineffective or even damaged; if L2>0.5c, the width of the spoiler 2 is too large to exceed the turbulent flow region of the air flow, disturbing the air flow in the laminar flow region and generating greater noise. Therefore, if 0.05c≤L2≤0.5c, the use strength of the spoiler 2 can be improved, the service life of the spoiler 2 can be extended, and at the same time, the noise reduction effect of the spoiler 2 can be improved to ensure the normal operation of the spoiler 2 .

If the leading edge 11 and the trailing edge 12 of the blade 1 are parallel, then the span direction of the blade 1, the chord length c per unit length is a constant value, if the shape of the leading edge 11 and the trailing edge 12 of the blade 1 changes If the rules are different, the chord length c per unit length is constantly changing. Therefore, the width L2 of the spoiler 2 can be a constant value, or it can be constantly changing.

Exemplarily, as shown in FIG. 2 and FIG. 3 , along the chord length direction of the blade 1 , the spoiler 2 includes a first side wall 21 and a second side wall 22 oppositely arranged, and at least part of the first side wall 21 is zigzag, and/or, at least part of the second side wall 22 is zigzag.

In this embodiment, at least part of the first side wall 21 is zigzag, and/or, at least part of the second side wall 22 is zigzag, and the zigzag first side wall 21 and/or the second side can be added. The contact area between the wall 22 and the airflow improves the noise reduction effect of the spoiler 2 , thereby improving the performance of the propeller.

Exemplarily, as shown in FIG. 2 , at least part of the first side wall 21 is straight, and/or at least part of the second side wall 22 is straight. It should be understood that the saw-tooth shape and the straight shape here are examples, and are not used to limit the shape of the side wall of the spoiler 2. In the embodiment of the present application, on the premise that the spoiler 2 can disturb the airflow, select Any suitable shape can be used as the shape of the side wall of the spoiler 2 .

Exemplarily, as shown in FIG. 3, the spoiler 2 includes a first side 23 and a second side 24, and a plurality of first sides 23 and a plurality of second sides 24 are arranged at intervals and connected to each other to form a zigzag first side. The angle α between the side wall 21 and/or the second side wall 22 ; the first side 23 and the second side 24 satisfies: 10°<α<120°.

In this embodiment, the first side 23 and the second side 24 are spaced apart and connected end to end to form a zigzag first side wall 21 and/or second side wall 22 . If the angle α between the first side 23 and the second side 24 is too large or too small, that is, the distance S between the adjacent tooth tips is too large or too small, the first side 23 and the second side 24 will be separated from the airflow. If the contact area is too small, the noise reduction effect of the spoiler 2 will be reduced. Therefore, 10°<α<120° can increase the contact area between the zigzag-shaped first side wall 21 and/or the second side wall 22 and the airflow, thereby improving the noise reduction effect of the spoiler 2 and further improving the use of the propeller. performance.

In any of the above embodiments, along the thickness direction of the blade 1, the blade 1 includes a top surface and a bottom surface oppositely arranged, both the top surface and the bottom surface are suction surfaces, and the spoiler 2 is arranged on the top surface, or the spoiler 2 Set on top and bottom.

In this embodiment, during the working process of the propeller, along the thickness direction of the blade 1, the noise generated above the propeller is greater than the noise generated below the propeller. Therefore, the spoiler 2 is set on the top surface of the blade 1, which can improve The noise reduction effect of the spoiler 2, the spoiler 2 is arranged on the top surface and the bottom surface, so that the noise above and below the propeller is reduced, thereby further improving the noise reduction effect of the spoiler 2 . Of course, as an example, the spoiler 2 can also be provided only on the bottom surface of the blade 1, so that the noise below the propeller is reduced, and the sum of the noise above and below the propeller will also be reduced, thereby reducing the noise. noise effect.

In any of the above embodiments, along the span direction of the blade 1 , the spoiler 2 runs through the blade 1 , or the spoiler 2 covers a part of the blade 1 . Wherein, the spoiler 2 runs through the blade 1, that is, the spoiler 2 covers the entire blade 1 in the span direction, or in other words, the projected length of the spoiler 2 in the span direction is equal to that of the blade 1 in the span direction. Projection length.

In this embodiment, along the span direction of the blade 1 , the spoiler 2 may pass through the blade 1 , or may only cover a part of the blade 1 , thereby increasing the flexibility of disposing the spoiler 2 . The spoiler 2 runs through the blade 1 along the span direction of the blade 1, which can increase the range of action of the spoiler 2, thereby improving the working performance of the spoiler 2, and reducing the noise generated when the propeller is in operation to a greater extent. The spoiler 2 covers a part of the blade 1, while meeting the noise reduction requirements of the propeller, the size of the spoiler 2 is reduced, thereby reducing the production cost of the spoiler 2, and at the same time reducing the weight of the spoiler 2 , thereby reducing the weight of the propeller and increasing the performance of the propeller.

Exemplarily, the number of the spoiler 2 is one or more; a plurality of spoilers 2 are arranged at intervals or continuously. The embodiment of the present application does not limit the number and arrangement of the spoiler 2 . When the number of the spoiler 2 is one, the shape of the side walls of the one spoiler 2 may be the same or different. For example, all the sidewall shapes of the spoiler 2 are zigzag, or all sidewall shapes are straight, or half of the sidewall shapes are zigzag and the other half of the sidewall shapes are straight, here Not limited. When there are multiple spoiler parts 2, the side wall shapes of different spoiler parts 2 include but are not limited to: the side walls of every two spoiler parts 2 have the same shape, or the sides of every two spoiler parts 2 The shapes of the walls are all different, or a part of the spoiler 2 has the same side wall shape and another part of the spoiler 2 has a different side wall shape, which will not be repeated here.

In this embodiment, the number of spoilers 2 is one or more; multiple spoilers 2 are arranged at intervals or continuously, which increases the flexibility of disposing the spoilers 2 on the blade 1 . A plurality of turbulent parts 2 are arranged at intervals, while ensuring the noise reduction performance of the turbulent parts 2, the material of the turbulent parts 2 is reduced, thereby reducing the production cost.

Exemplarily, when there are multiple spoilers 2, all the spoilers 2 may be arranged at intervals, or all the spoilers 2 may be arranged continuously, or some spoilers 2 may be arranged at intervals and the other part may be arranged at intervals. The spoiler 2 is arranged continuously, and the setting method is relatively flexible, and an appropriate setting method can be selected according to experience or actual needs.

In any of the above embodiments, the spoiler 2 is integrally formed or fixedly connected to the paddle 1 . Exemplarily, the fixed connection includes: obtaining a separate spoiler 2 and a separate paddle 1 , and then assembling the spoiler 2 to the paddle 1 so that the spoiler 2 is fixedly connected to the paddle 1 .

In this embodiment, the spoiler 2 is integrally formed with the blade 1, which increases the stability of the connection between the spoiler 2 and the blade 1, and prevents the spoiler 2 from being separated from the blade 1 during the operation of the propeller. Safety issues, thereby improving the stability of the propeller and the safety of use. The spoiler 2 is fixedly connected to the paddle 1 , which can facilitate the processing of the spoiler 2 and the paddle 1 , thereby reducing the processing cost of the spoiler 2 and the paddle 1 . The spoiler 2 is integrally formed or fixedly connected with the blade 1 , which increases the connection mode between the spoiler 2 and the blade 1 , thereby increasing the flexibility of connecting the spoiler 2 and the blade 1 .

Exemplarily, if there are multiple spoiler parts 2, when there are multiple spoiler parts 2, all spoiler parts 2 may be integrally formed with the blade 1, or all spoiler parts 2 may be integrated with the The paddle 1 is fixedly connected, or a part of the spoiler 2 is integrally formed with the paddle 1 and another part of the spoiler 2 is fixedly connected with the paddle 1 .

The embodiment of the present application also provides an aircraft, the aircraft includes a body and a propeller, the propeller is the propeller described in any of the above embodiments; the propeller is installed on the body.

In this embodiment, a spoiler 2 extending along the chord direction of the blade 1 is provided on the propeller to increase the turbulent flow velocity, so that the area where noise is generated on the surface of the blade 1 is reduced, thereby reducing the noise generated during the working process of the propeller. In turn, the performance of the aircraft can be improved, and at the same time, the concealment of the aircraft can be improved, thereby improving the application scenarios of the aircraft. That is, improving the versatility of the aircraft makes the aircraft applicable to more scenarios and expands the scope of application of the aircraft.

Exemplarily, the aircraft includes, but is not limited to: a multi-rotor type aircraft, a vertical take-off and landing type aircraft, and the like. Wherein, the multi-rotor type aircraft includes multiple rotor shafts, and the above-mentioned body and propeller can be connected through the rotor shafts. Certainly, the embodiment of the present application does not limit the type of the aircraft, as long as the aircraft can use propellers.

The above description is only an embodiment of the present application, and is not intended to limit the present application. For those skilled in the art, the present application may have various modifications and changes. Any modifications, equivalent replacements, improvements, etc. made within the principles of this application shall be included within the scope of protection of this application.

Claims

A propeller, wherein the propeller comprises:

paddle (1);

A spoiler (2), at least part of the spoiler (2) protrudes from the suction surface of the blade (1);

Wherein, the spoiler (2) extends along the span direction of the blade (1).
The propeller according to claim 1, wherein, along the chord direction of the blade (1), the blade (1) further comprises a leading edge (11) and a trailing edge (12) arranged oppositely, the The vertical distance between the leading edge (11) and the trailing edge (12) is the chord length c of the blade (1), and the centerline of the spoiler (2) and the leading edge (11) The distance L1 between them satisfies: 0.05c≤L1≤0.6c.
The propeller according to claim 1, wherein, along the chord direction of the blade (1), the blade (1) further comprises a leading edge (11) and a trailing edge (12) arranged oppositely, the The vertical distance between the leading edge (11) and the trailing edge (12) is the chord length c of the blade (1), the Reynolds number of the operating environment of the propeller is Re, and the spoiler (2) The height of the protruding suction surface is h to satisfy: h=kc/Re 0.2 ;

Wherein, the proportional coefficient k satisfies: 0.01≤k≤0.2.
The propeller according to claim 1, wherein, along the chord direction of the blade (1), the blade (1) further comprises a leading edge (11) and a trailing edge (12) arranged oppositely, the The vertical distance between the leading edge (11) and the trailing edge (12) is the chord length c of the blade (1), and the width L2 of the spoiler (2) satisfies: 0.05c≤L2≤0.5 c.
The propeller according to claim 1, wherein, along the chord direction of the blade (1), the spoiler (2) comprises a first side wall (21) and a second side wall (22) arranged opposite to each other ), at least part of the first side wall (21) is zigzag, and/or, at least part of the second side wall (22) is zigzag.
The propeller according to claim 5, wherein the spoiler (2) comprises a first side (23) and a second side (24), a plurality of said first sides (23) and a plurality of said second sides (24) The first side wall (21) and/or the second side wall (22) are arranged at intervals and connected to each other to form a zigzag shape;

The angle α between the first side (23) and the second side (24) satisfies: 10°<α<120°.
The propeller according to any one of claims 1-6, wherein, along the thickness direction of the blade (1), the blade (1) includes a top surface and a bottom surface oppositely arranged, and the top surface and the Both the bottom surfaces are the suction surfaces, and the spoiler (2) is arranged on the top surface, or the spoiler (2) is arranged on the top surface and the bottom surface.
The propeller according to any one of claims 1-6, wherein, along the span direction of the blade (1), the spoiler (2) penetrates the blade (1), or, the The spoiler (2) covers a part of the paddle (1).
The propeller according to claim 8, wherein the number of the spoiler (2) is one or more;

Multiple spoilers (2) are arranged at intervals or continuously.
The propeller according to any one of claims 1-6, wherein the spoiler (2) is integrally formed or fixedly connected to the blade (1).
An aircraft, wherein the aircraft comprises a body and the propeller according to any one of claims 1-10;

The propeller is installed on the body.