阅读说明：本技术 一种用于推迟大展弦比机翼失速迎角的涡流发生器及方法 (Vortex generator and method for delaying stall attack angle of high-aspect-ratio wing ) 是由 赵艳平 肖良华 陈瑶 闫林明 陈蕊 夏生林 冯文梁 于 2020-06-22 设计创作，主要内容包括：本发明提出了一种用于推迟大展弦比机翼失速迎角的涡流发生器及方法,安装在大展弦比后掠机翼上,所述涡流发生器为一片厚度为w的面板,包括一体连接的矩形面板部分CDBI、圆弧扇形直角面板部分ACI；本发明通过上述设置实现了延缓气流分离,推迟失速,提高最大可用升力系数的效果。(The invention provides a vortex generator and a method for delaying a stall attack angle of a high-aspect-ratio wing, wherein the vortex generator is arranged on a high-aspect-ratio sweepback wing, is a panel with the thickness of w, and comprises a rectangular panel part CDBI and an arc sector right-angle panel part ACI which are integrally connected; according to the invention, the effects of delaying airflow separation, delaying stall and improving the maximum available lift coefficient are realized through the arrangement.)

1. A vortex generator for delaying the stall attack angle of a high-aspect-ratio wing is installed on a high-aspect-ratio sweepback wing, and is characterized in that the vortex generator is a panel with the thickness of w and comprises a rectangular panel part CDBI and an arc sector right-angle panel part ACI which are integrally connected; the longest edge of the panel with the thickness of w is the side length AB;

the rectangular panel part CDBI is a rectangular panel, and the bottom side length IB of the rectangular panel is L2, and the side length BD of the rectangular panel is h;

the length IC of one right-angle side of the arc fan-shaped right-angle panel part ACI connected with the rectangular panel part CDBI is h, and the length AI of the other right-angle side not connected with the rectangular panel part CDBI is L3; the length of an arc edge AC formed by the two right-angle side lengths AI and the right-angle side length IC is s; the length of the side length AB is L2+ L3.

2. The vortex generator of claim 1, wherein the arc edge AC is divided into two segments, one segment being an arc AK and one segment being an arc KC, wherein the arc AK is located on a parabola AMD, wherein the parabola AMD is a parabola connecting A, D two points and having a focus on the side length AB.

3. The vortex generator for delaying the stall angle of attack of a high aspect ratio wing according to claim 2, wherein the arc section AK is a curve having two end points A, K with a distance h equal to 3% to 5%.

4. A vortex generator for delaying the stall angle of attack of a high aspect ratio wing according to claim 3, wherein the arc KC is a curve tangent to the arc AK at point K and to the edge length CD of the rectangular panel portion CDBI at point C.

5. A manufacturing approach of the vortex generator, is used for making the above-mentioned vortex generator, characterized by that, calculate and produce the plane shape ABDC of the vortex generator at first; generating a vortex generator with the thickness of w according to the planar ABDC;

when calculating the planar shape ABDC, firstly, the length h of the side edge length BD of the rectangular panel part CDBI is required to be calculated, and the length h of the right-angle edge length IC connected with the circular arc sector right-angle panel part ACI and the rectangular panel part CDBI is also required to be calculated; the length of the length h is determined according to the thickness of the boundary layer at the wing station where the vortex generator is placed, and is slightly larger than or equal to the thickness of the local boundary layer.

6. The method of manufacturing a vortex generator as claimed in claim 5, wherein after the value of h is calculated, the length of L2+ L3 is further calculated; the length of the L2+ L3 is set to be 3-5 times of h.

7. The method of claim 6, wherein the length of L2 is further calculated after the length of L2+ L3 is determined, the length of L2 is 50% to 70% of the length of L2+ L3; after the length of L2 was determined, the length of L3 was calculated.

8. The method of manufacturing a vortex generator according to claim 7, wherein after the values of h, L1, L2, L3 are determined, the length of the arc edge AC is further calculated; the specific calculation steps of the arc edge AC are as follows:

s1, constructing an auxiliary line AMD, wherein the auxiliary line AMD is a parabola, the focus of which is on a side length AB with the length of L1 and the connection point A and the point D are connected;

s2, selecting a curve section AK on an auxiliary line AMD, wherein the length of the curve section AK is 3% -5% of h;

s3, after the curve section AK is determined, determining an arc section KC according to the curve section AK and the side length CD; the arc section KC is a curve tangent to the arc section AK at a point K and tangent to the side length CD of the CDBI of the rectangular panel part at a point C.

9. A method for installing and using a vortex generator is suitable for installing the vortex generator and is characterized in that the vortex generator is installed on the front edge of a large-aspect-ratio small-sweep wing, and an included angle of the vortex generator and an incoming flow direction is 10-30 degrees.

10. The method for installing and using the vortex generator as claimed in claim 9, wherein when a plurality of vortex generators are installed at the same time, the distance between each two vortex generators is set to be 2.5% to 10% of the half span length.

Technical Field

The invention belongs to the field of aviation, and particularly relates to a vortex generator for delaying a stall attack angle of a high-aspect-ratio wing.

Background

The wings of modern passenger planes are usually provided with a plurality of vortex generators, which are actually small wings with small aspect ratio and vertically arranged on the surface of the plane at a certain installation angle, and due to the small aspect ratio, the incoming flow flows through the surfaces of the vortex generators to generate stronger wingtip vortexes, and the high-energy wingtip vortexes can roll high-energy fluid outside the boundary layers into the boundary layers, so that the boundary layers in the inverse pressure gradient can be continuously attached to the surfaces of the wings after obtaining additional energy without separation, flow separation on the upper surfaces of the wings is delayed or inhibited, stall is delayed, stall attack angle is delayed, maximum lift coefficient is improved, and aerodynamic wing characteristics are enhanced.

Most of the conventional vortex generators are designed for wind turbine blades and wings of large civil airliners, the wind turbine blades are large in relative thickness (12-40%), the large civil airliners are medium in aspect ratio (7-9), and large in sweepback angle (25-30 ℃), and the vortex generators are not suitable for large aspect ratio and small sweepback wings. At present, no vortex generator is seen on the aircrafts with large aspect ratio and small sweepback wings at home and abroad.

Disclosure of Invention

The invention provides a vortex generator and a method for delaying the stall attack angle of a high-aspect-ratio wing aiming at the blank of a vortex generator technology on a high-aspect-ratio and small-sweep wing in the prior art.

The specific implementation method of the invention is as follows:

the invention provides a vortex generator for delaying the stall attack angle of a high-aspect-ratio wing, which is arranged on a high-aspect-ratio sweepback wing, is a panel with the thickness of w, and comprises a rectangular panel part CDBI and an arc sector right-angle panel part ACI which are integrally connected; the longest edge of the panel with the thickness of w is the side length AB;

the rectangular panel part CDBI is a rectangular panel, and the bottom side length IB of the rectangular panel is L2, and the side length BD of the rectangular panel is h;

the length IC of one right-angle side of the arc fan-shaped right-angle panel part ACI connected with the rectangular panel part CDBI is h, and the length AI of the other right-angle side not connected with the rectangular panel part CDBI is L3; the length of an arc edge AC formed by the two right-angle side lengths AI and the right-angle side length IC is s; the length of the side length AB is L2+ L3.

In order to better implement the present invention, further, the arc edge AC is divided into two segments, one segment is an arc segment AK, and the other segment is an arc segment KC, where the arc segment AK is located on a parabola AMD, and the parabola AMD is a parabola which connects A, D two points and has a focus on the side length AB.

In order to better implement the present invention, further, the arc section AK is a curve with a distance between two end points A, K equal to 3% to 5% of h.

In order to better implement the present invention, further, the arc segment KC is a curve tangent to the arc segment AK at the point K and tangent to the side length CD of the rectangular panel portion CDBI at the point C.

The invention also provides a manufacturing method of the vortex generator, which is used for manufacturing the vortex generator and comprises the steps of firstly calculating and generating the planar ABDC of the vortex generator; generating a vortex generator with the thickness of w according to the planar ABDC;

when calculating the planar shape ABDC, firstly, the length h of the side edge length BD of the rectangular panel part CDBI is required to be calculated, and the length h of the right-angle edge length IC connected with the circular arc sector right-angle panel part ACI and the rectangular panel part CDBI is also required to be calculated; the length of the length h is determined according to the thickness of the boundary layer at the wing station where the vortex generator is placed, and is slightly larger than or equal to the thickness of the local boundary layer.

In order to better implement the present invention, further, after the value of h is calculated, the length of L2+ L3 is further calculated; the length of the L2+ L3 is set to be 3-5 times of h.

In order to better implement the invention, further, after the length of L2+ L3 is determined, the length of L2 is further calculated, wherein the length of L2 is 50% -70% of the length of L2+ L3; after the length of L2 was determined, the length of L3 was calculated.

In order to better implement the invention, further, after the values of h, L1, L2 and L3 are determined, the length of the arc edge AC is further calculated; the specific calculation steps of the arc edge AC are as follows:

s1, constructing an auxiliary line AMD, wherein the auxiliary line AMD is a parabola, the focus of which is on a side length AB with the length of L1 and the connection point A and the point D are connected;

s2, selecting a curve section AK on an auxiliary line AMD, wherein the length of the curve section AK is 3% -5% of the length h;

s3, after the curve section AK is determined, determining an arc section KC according to the curve section AK and the side length CD; the arc section KC is a curve tangent to the arc section AK at a point K and tangent to the side length CD of the CDBI of the rectangular panel part at a point C.

The invention also provides a mounting and using method of the vortex generator, which is suitable for mounting the vortex generator, wherein the vortex generator is mounted at the front edge of the large-aspect-ratio small-sweep wing, and the included angle between the vortex generator and the incoming flow direction is 10-30 degrees.

In order to better implement the present invention, further, when a plurality of vortex generators are simultaneously installed, the distance between each two vortex generators is set to be 2.5% to 10% of the half span length.

Compared with the prior art, the invention has the following advantages and beneficial effects:

(1) the technical blank of the vortex generator on the large-aspect-ratio and small-sweep wing in the prior art is made up;

(2) the airflow separation of the aircraft is delayed;

(3) stall is postponed;

(4) the maximum available lift coefficient of the aircraft is improved.

Drawings

Figure 1 is a front view of a vortex generator;

FIG. 2 is a top view of the vortex generator;

figure 3 is a perspective view of a vortex generator;

FIG. 4 is a schematic view of an auxiliary line labeled AMD;

FIG. 5 is a schematic view of vortex generators arranged on a wing;

FIG. 6 is an exemplary schematic view of a vortex generator disposed on a wing;

FIG. 7 is a schematic diagram comparing the lift lines before and after mounting the vortex generator;

FIG. 8 is a pressure cloud and a flow chart of the outer section of the upper surface of the airfoil without the vortex generator installed at an angle of attack of 12 °;

fig. 9 is a pressure cloud and a flow chart of the outer section of the upper surface of the wing after the vortex generator is installed when the attack angle is 12 degrees.

Detailed Description

In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it should be understood that the described embodiments are only a part of the embodiments of the present invention, and not all embodiments, and therefore should not be considered as a limitation to the scope of protection. All other embodiments, which can be obtained by a person skilled in the art without any inventive step based on the embodiments of the present invention, are within the scope of the present invention.

In the description of the present invention, it is to be noted that, unless otherwise explicitly specified or limited, the terms "disposed," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.