CN217945500U - Vortex generator for improving wing surface flow characteristics of electric vertical take-off and landing aircraft - Google Patents

Abstract

The utility model discloses a vortex generator for improving electronic VTOL aircraft airfoil flow characteristic, including the vortex generator body, the vortex generator body includes a plurality of vortex generator thin slices, and is a plurality of the array is constituteed to the vortex generator thin slice, installs on the wing, there is contained angle theta in vortex generator thin slice and vertical direction, contained angle theta is not more than 30. The vortex generator can effectively increase the lift coefficient and the stall attack angle; the vortex generator can improve the flow separation of the airfoil under a large attack angle and reduce the aerodynamic noise and structural vibration caused by the flow separation.

Description

Vortex generators for improving airfoil flow characteristics of electric vertical take-off and landing aircraft

technical field

The utility model relates to the technical field of aviation equipment, in particular to a vortex generator for improving the flow characteristics of the wing surface of an electric vertical take-off and landing aircraft.

Background technique

eVTOL (Electric Vertical Takeoff and Landing) electric vertical takeoff and landing aircraft applications involve urban passenger transport, regional passenger transport, freight, personal aircraft, emergency medical services and other scenarios.

There are three main configurations of eVTOL, namely multi-rotor, compound wing, and tilting wing configuration. Multi-rotors use multiple propellers to realize eVTOL takeoff, landing, and level flight. The eVTOL mission profile usually involves the mutual conversion between multi-rotor and fixed wing. For the fixed wing and conversion phase, the aircraft needs to have sufficient stall margin. Due to the blockage of the motor arm and the propeller, the energy of the airflow on the airfoil on the wing is weakened. Usually, with the increase of the angle of attack, the flow separation phenomenon will occur on the trailing edge of the fixed wing airfoil, and the separation area will further expand with the increase of the angle of attack. If not controlled, it will cause the aircraft to enter a stall. Therefore, to improve the low-speed characteristics of the aircraft during the electric vertical take-off and landing phase, the airfoil flow separation of the wings must be improved.

Airfoil flow separation refers to the phenomenon that the airflow does not adhere to the surface in certain areas on the airfoil. The separation will cause the lift to deviate from linearity, increase the drag, and cause increased noise and structural vibration problems. If the separation develops further and expands, it will cause the aircraft to stall. Stall refers to the flight condition corresponding to when the aircraft reaches the maximum available lift coefficient. The stall state of an aircraft is usually defined by the stall angle of attack or stall speed. During a stall condition, uncommanded roll, pitch, or yaw motion of the aircraft may occur. Therefore, it is necessary to ensure that the aircraft has sufficient margin during flight to prevent entering a stall.

The vortex generator is a device to improve the flow separation of the boundary layer. Its principle is to inject the high-energy fluid outside the boundary layer into the low-energy flow inside the boundary layer, so that the boundary layer obtains high energy from the outside, thereby improving the anti-separation ability of the boundary layer . However, the structure of the existing vortex launcher is complex, which increases the weight of the system and the complexity of the control for the electric vertical take-off and landing aircraft. Therefore, it is urgent to develop a flow separation improvement device with simple structure, light weight and simple control (or without control).

Utility model content

The purpose of the utility model is to provide a vortex generator for improving the airfoil flow characteristics of an electric vertical take-off and landing aircraft, so as to solve the problems mentioned in the background technology. In order to achieve the above object, the utility model provides the following technical solutions: the vortex generator used to improve the airfoil flow characteristics of the electric vertical take-off and landing aircraft includes a vortex generator body, and the vortex generator body includes a plurality of vortex generator sheets, A plurality of vortex generator slices form an array and are installed on the wing. The vortex generator slices have an included angle θ with the vertical direction, and the included angle θ is not greater than 30°.

Preferably, the minimum height of the top of the vortex generator sheet is h, the width is w, and the distance between adjacent vortex generator sheets is d, wherein d/w≥1 and w/h≥3.

Preferably, the vortex generator body is mounted upstream of the airfoil separation zone on the wing.

The technical effects and advantages of the utility model: the vortex generator can effectively increase the lift coefficient and the stall angle of attack; the vortex generator can improve the flow separation of the airfoil at a large angle of attack, and reduce the aerodynamic noise and structural vibration caused by the flow separation.

Description of drawings

Fig. 1 is a schematic diagram of the installation position of the utility model;

Figure 2 is an enlarged view of the top view of the installation position of the utility model;

Fig. 3 is a side view of the installation position of the utility model;

Fig. 4 is a schematic diagram of the size of the vortex generator sheet of the present invention;

Fig. 5 is a schematic diagram of the wake vortex of the present invention.

In the figure, 1-wing; 2-propeller; 3-fuselage; 4-vortex generator body; 5-motor arm; 6-vortex generator sheet.

detailed description

In order to make the technical means, creative features, goals and effects of the utility model easy to understand, the utility model will be further elaborated below in conjunction with specific diagrams. In the description of the utility model, it should be noted that unless otherwise specified The terms "installation", "connection" and "connection" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection or a mechanical connection, or an electrical connection ; It can be directly connected, or indirectly connected through an intermediary, and can be connected internally between two components.

Example

As shown in Figure 1, it is a typical electric vertical take-off and landing compound wing structure. Due to the interference of the fuselage 3, especially the close coupling between the propeller 2 and the motor arm 5 and the wing 1, the wing surface is compared with that of the clean wing. Separate early. A vortex generator 4 is mounted upstream of the airfoil separation zone on the wing 1 . The vortex generator 4 includes a plurality of vortex generator slices 6 to form an array, which is at an angle to the incoming flow, and its height generally exceeds the boundary layer height. The wake vortex generated by it at a large angle of attack makes the wing 1 airfoil separation flow adhere again , to delay the occurrence of separation.

As shown in Figures 2 to 4, it is a schematic arrangement of vortex generators 4, wherein there is an angle θ between the vortex generator sheet and the vertical direction, generally the included angle θ is not greater than 30°; the minimum height of the top of the vortex generator sheet 6 is h , the width is w, and the distance between adjacent vortex generator slices 6 is d, where d/w≥1 and w/h≥3.

The wake vortex of the vortex generator is shown in Figure 5. While injecting energy into the boundary layer, its high-speed rotating flow also generates a corresponding downwash flow, which makes the downstream separation flow closer to the wall, and then adheres to it, increasing the lift and stall angle of attack. Therefore, its position is not limited to that shown in FIG. 1 . Its chordwise position is generally placed before the separation zone, but it does not have to be close to the leading edge of the wing; its spanwise position depends on the separation position of the wing surface, which is related to the separation characteristics of the wing surface, and is different for different wings or different aircraft.

Finally, it should be noted that: the above is only a preferred embodiment of the utility model, and is not intended to limit the utility model, although the utility model has been described in detail with reference to the foregoing embodiments, for those skilled in the art , it can still modify the technical solutions recorded in the foregoing embodiments, or perform equivalent replacements on some of the technical features. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principles of the present utility model, All should be included within the protection scope of the present utility model.

Claims (3)

1. The vortex generator for improving the airfoil flow characteristics of an electric vertical take-off and landing aircraft comprises a vortex generator body, characterized in that: the vortex generator body comprises a plurality of vortex generator slices, and a plurality of the vortex generators The slices form an array and are installed on the wing. The vortex generator slices have an included angle θ with the vertical direction, and the included angle θ is not greater than 30°. 2. The vortex generator for improving the airfoil flow characteristics of an electric vertical take-off and landing aircraft according to claim 1, characterized in that: the minimum height of the top of the vortex generator sheet is h, the width is w, and adjacent vortexes occur The distance between the device sheets is d, where d/w≥1 and w/h≥3. 3. The vortex generator for improving the airfoil flow characteristics of an electric vertical take-off and landing aircraft according to claim 1, characterized in that: the vortex generator body is installed upstream of the airfoil separation area on the wing.

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