CN112896489B - Slotted guide vane type high lift device - Google Patents
Slotted guide vane type high lift device Download PDFInfo
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- CN112896489B CN112896489B CN202110189450.XA CN202110189450A CN112896489B CN 112896489 B CN112896489 B CN 112896489B CN 202110189450 A CN202110189450 A CN 202110189450A CN 112896489 B CN112896489 B CN 112896489B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/28—Leading or trailing edges attached to primary structures, e.g. forming fixed slots
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/58—Wings provided with fences or spoilers
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Abstract
The invention provides a slotted guide vane type high lift device, wherein slots are formed in the upper surface and the lower surface of an airfoil; performing rounding and shape modification treatment on a seam A1 point, a seam B1 point, a seam C1 point, a seam B2 point and a seam C2 point; performing second rounding shape modification treatment at the position of the slot on the rear part of the wing profile of the slot wing, namely the position of a slot opening A1, wherein the radius range of an inscribed circle is 0.05 c-0.4 c, and the rounding after cutting forms a flow deflector; and (3) moving the guide vane upwards along the normal direction of the local lower surface of the thickest position of the guide vane within the moving range of 0.005 c-0.2 c to finally form the layout of increasing the guide vane at the slit opening, thus obtaining the slit guide vane type high lift device. The slotted guide vane type high lift device provided by the invention can obviously improve the maximum lift coefficient of the wing profile, greatly improves the stall characteristic of the wing profile, is a simple and efficient novel high lift device, and further effectively improves the aerodynamic performance and the control stability of an aircraft.
Description
Technical Field
The invention belongs to the technical field of wing section design, and particularly relates to a slotted guide vane type high lift device.
Background
At present, the traditional high lift device usually adopts a multi-section wing structure form, the mechanism is heavy and complex, the weight of the aircraft is increased, the engineering efficiency is not high enough, and the requirement of the existing aircraft for high-efficiency landing and flying can not be met.
In order to solve the above problems, a slotted airfoil appears in the prior art, as shown in fig. 1, which is a structure diagram of a slotted airfoil appearing in the prior art, and the principle thereof is as follows: one part of the whole wing profile is deducted, so that the aim of slotting is fulfilled. Slitting airfoils is a passive flow control method. However, the existing slotted airfoil has limited lift-increasing effect, namely: the effect of improving the maximum lift coefficient is limited, and the effect of improving the airfoil stall characteristic is limited, so that the effects of improving the aerodynamic performance and controlling the stability of the aircraft are limited.
Disclosure of Invention
Aiming at the defects in the prior art, the invention provides a slotted guide vane type high lift device which can effectively solve the problems.
The technical scheme adopted by the invention is as follows:
the invention provides a slotting guide vane type high lift device, wherein a slot is formed in the upper surface and the lower surface of an airfoil, the slotting range of the upper surface of the airfoil is within the range of 0.15c after the maximum thickness position of the airfoil, and the slotting range of the lower surface of the airfoil is within the range of 0.15c before the maximum thickness position of the airfoil; c is the chord length of the airfoil; the width range of the seam is 0.01 c-0.2 c; the central line of the seam channel inclines to the trailing edge of the airfoil, and the included angle between the central line of the seam channel and the upper surface of the airfoil ranges from 10 degrees to 50 degrees and the included angle between the central line of the seam channel and the lower surface of the airfoil ranges from 50 degrees to 90 degrees;
the boundaries of two sides of the slot way along the front and back directions are the boundary of the front side of the slotted wing slot way and the boundary of the back side of the slotted slat slot way respectively; the intersection point of the front boundary of the slat opening slot and the upper surface of the wing profile is a slot opening A2; the intersection point of the front boundary of the slat opening slot and the lower surface of the airfoil profile is a slot opening B2; the upper boundary line of the front side boundary of the slotted wing channel and the upper surface of the wing profile form an included angle, the lower boundary line of the front side boundary of the slotted wing channel and the lower surface of the wing profile form an included angle, and the upper boundary line of the front side boundary of the slotted wing channel and the lower boundary line of the front side boundary of the slotted wing channel intersect at a point C2; thus, the slotted-gate leading-side boundary is made up of the upper boundary line A2C2 of the slotted-gate leading-side boundary and the lower boundary line C2B2 of the slotted-gate leading-side boundary;
the intersection point of the rear boundary of the slat opening slot and the upper surface of the wing profile is a slot opening A1; the intersection point of the rear boundary of the slat opening slot and the lower surface of the wing profile is a slot opening B1; the upper boundary line of the rear side boundary of the slat opening slot way and the upper surface of the wing profile form an included angle, the lower boundary line of the rear side boundary of the slat opening slot way and the lower surface of the wing profile form an included angle, and the upper boundary line of the rear side boundary of the slat opening slot way and the lower boundary line of the rear side boundary of the slat opening slot way intersect at a point C1; thus, the slotted throat rear boundary consists of the upper boundary line A1C1 of the slotted throat rear boundary and the lower boundary line C1B1 of the slotted throat rear boundary;
performing rounding and shape modification treatment on a seam opening A1, a seam opening B1 and a point C1, a seam opening B2 and a point C2 to obtain a seam wing shape after seam modification;
then, performing second rounding shape modification treatment at the position of the slot on the rear part of the wing profile of the slot wing, namely the position of a slot opening A1, wherein the radius range of an inscribed circle is 0.05 c-0.4 c, and the rounding after cutting forms a flow deflector;
and (3) moving the guide vane upwards along the normal direction of the local lower surface of the thickest position of the guide vane within the moving range of 0.005 c-0.2 c to finally form the layout of increasing the guide vane at the slit opening, thus obtaining the slit guide vane type high lift device.
Preferably, the rounding treatment of the seam opening A1, the seam openings B1 and C1 points, and the seam openings B2 and C2 points is as follows:
c1 point is rounded off and modified, the radius of the removed rounded off is 0.01C-0.3C;
c2 point is rounded and supplemented with shape, the radius of added rounding is 0.01C-0.3C;
the seam road opening A1 is subjected to rounding removal and shape modification treatment, and the radius of the removed rounding is 0.01 c-0.1 c;
rounding, removing and modifying the seam crossing B1, wherein the radius of the removed rounding is 0.01 c-0.1 c;
and rounding, removing and modifying the seam opening B2, wherein the radius of the removed rounding is 0.01 c-0.2 c.
Preferably, the slotted guide vane type high lift device is suitable for the airfoil with the thickness of more than 0.12 c.
The slotted guide vane type high lift device provided by the invention has the following advantages:
the slotted guide vane type high lift device provided by the invention can obviously improve the maximum lift coefficient of the wing profile, greatly improves the stall characteristic of the wing profile, is a simple and efficient novel high lift device, and further effectively improves the aerodynamic performance and the control stability of an aircraft.
Drawings
FIG. 1 is a block diagram of a slotted airfoil as found in the prior art;
FIG. 2 is a schematic view of the design of a flow deflector for a slot road provided by the present invention;
FIG. 3 is a block diagram of a NACA4421 airfoil;
FIG. 4 is a schematic view of the position of the center line of the seam path in the present invention;
FIG. 5 is a schematic illustration of the slotted airfoil of the present invention prior to reshaping;
FIG. 6 is a schematic view of a slotted airfoil in accordance with the present invention after modification of the slot;
fig. 7 is a schematic view of the inventive slotted guide vane;
fig. 8 is a schematic view of the slotted guide vane type high lift device of the present invention.
Detailed Description
In order to make the technical problems, technical solutions and advantageous effects solved by the present invention more clearly apparent, the present invention is further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
The core idea of the invention is to provide a slotted guide vane type high lift device, firstly determining a slotted position; then, carrying out local shape modification on the seam; and finally, increasing the design of a flow deflector. Therefore, the arrangement of the guide vanes at the slit passage opening can realize the obvious improvement of the maximum lift coefficient of the airfoil profile, greatly improve the stall characteristic of the airfoil profile, and is a simple and efficient novel high-lift device.
The present invention is directed to an airfoil having a thickness of 0.12c or more (c being a chord length of the airfoil). As shown in fig. 2, a schematic view of the design of the flow guide plate added to the seam road provided by the present invention; wherein 1 represents a seam; 2 represents an airfoil; and 3 denotes a guide vane.
The invention provides a slotted guide vane type high lift device, which has the following structure:
(1) slotting position:
the slotting range of the upper surface of the airfoil is within 0.15c after the maximum thickness position of the airfoil, and the slotting range of the lower surface of the airfoil is within 0.15c before the maximum thickness position of the airfoil. c is the chord length of the airfoil;
the width of the seam is 0.01 c-0.2 c. The central line of the seam channel inclines to the trailing edge of the airfoil, and the included angle between the central line of the seam channel and the upper surface of the airfoil ranges from 10 degrees to 50 degrees and the included angle between the central line of the seam channel and the lower surface of the airfoil ranges from 50 degrees to 90 degrees.
(2) Shape modification in the seam path:
the boundaries of two sides of the slot way along the front and back directions are the boundary of the front side of the slotted wing slot way and the boundary of the back side of the slotted slat slot way respectively; the intersection point of the front boundary of the slat opening slot and the upper surface of the wing profile is a slot opening A2; the intersection point of the front boundary of the slat opening slot and the lower surface of the airfoil profile is a slot opening B2; the upper boundary line of the front side boundary of the slotted wing channel and the upper surface of the wing profile form an included angle, the lower boundary line of the front side boundary of the slotted wing channel and the lower surface of the wing profile form an included angle, and the upper boundary line of the front side boundary of the slotted wing channel and the lower boundary line of the front side boundary of the slotted wing channel intersect at a point C2; thus, the slotted-gate leading-side boundary is made up of the upper boundary line A2C2 of the slotted-gate leading-side boundary and the lower boundary line C2B2 of the slotted-gate leading-side boundary;
the intersection point of the rear boundary of the slat opening slot and the upper surface of the wing profile is a slot opening A1; the intersection point of the rear boundary of the slat opening slot and the lower surface of the wing profile is a slot opening B1; the upper boundary line of the rear side boundary of the slat opening slot way and the upper surface of the wing profile form an included angle, the lower boundary line of the rear side boundary of the slat opening slot way and the lower surface of the wing profile form an included angle, and the upper boundary line of the rear side boundary of the slat opening slot way and the lower boundary line of the rear side boundary of the slat opening slot way intersect at a point C1; thus, the slotted throat rear boundary consists of the upper boundary line A1C1 of the slotted throat rear boundary and the lower boundary line C1B1 of the slotted throat rear boundary;
performing rounding and shape modification treatment on a seam opening A1, a seam opening B1 and a point C1, a seam opening B2 and a point C2 to obtain a seam wing shape after seam modification;
specifically, the shape of the joint of the upper part and the lower part of the seam is as follows: rounding the points C1 and C2, rounding the back part of the wing profile of the slotted wing, namely the point C1, and trimming, wherein the radius of the removed rounding is 0.01-0.3C; the front part of the slotted wing profile, namely the point C2, is subjected to rounding supplement modification treatment, and the radius of the added rounding is 0.01C-0.3C;
the position of a slot on the rear part of the slat-opening wing section, namely a slot opening A1, is subjected to rounding, removing and modifying treatment, and the radius of the removed rounding ranges from 0.01c to 0.1 c;
the lower slot opening position of the rear part of the slat opening wing section, namely a slot opening B1, is subjected to rounding, removing and modifying treatment, and the radius range of the removed rounding is 0.01 c-0.1 c;
the lower slot opening position of the front part of the slat opening wing section, namely the slot opening B2, is subjected to rounding, removing and modifying treatment, and the radius of the removed rounding ranges from 0.01c to 0.2 c.
(3) Flow deflectors:
performing secondary rounding shape modification treatment on the slotting position on the rear part of the slat-opening wing section, namely the position of a slot way opening A1, wherein the radius range of an inscribed circle is 0.05 c-0.4 c, and the rounding after cutting forms a flow deflector;
and (3) moving the guide vane upwards along the normal direction of the local lower surface of the thickest position of the guide vane within the moving range of 0.005 c-0.2 c to finally form the layout of increasing the guide vane at the slit opening, thus obtaining the slit guide vane type high lift device.
The present invention is illustrated with a NACA4421 airfoil as an example, the airfoil having a maximum thickness position of 0.3c and a maximum thickness of 0.21 c. The base airfoil, which is not slotted, is shown in FIG. 3.
The first step is as follows: a seam center line is determined.
Selecting the intersection point of the center line of the seam path and the upper surface of the wing profile as 0.4c, and recording the intersection point as a point A; and selecting the intersection point position of the seam path central line and the lower surface of the airfoil profile as 0.2c, and recording the intersection point position as a point B. The intersection angles of the center line of the seam way and the upper and lower wing surfaces are respectively 30 degrees and 60 degrees, and the intersection angles are intersected at the point C in the seam way to form a seam way center line A-C-B as shown in figure 4.
The second step is that: forming a seam.
A cylindrical seam with a width of 0.05C is formed with the seam centerline A-C-B as the center, and the resulting slotted airfoil is shown in FIG. 5.
The boundaries of two sides of the slot way along the front and back directions are the boundary of the front side of the slotted wing slot way and the boundary of the back side of the slotted slat slot way respectively; the boundary of the front side of the slat opening seam is a boundary line A2-C2-B2; the boundary of the rear side of the slat opening seam is a boundary line A1-C1-B1; the boundary line A2-C2-B2 and the boundary line A1-C1-B1 are two parallel boundary line segments.
The intersection point of the front boundary of the slat opening slot and the upper surface of the wing profile is a slot opening A2; the intersection point of the front boundary of the slat opening slot and the lower surface of the airfoil profile is a slot opening B2; the upper boundary line of the front side boundary of the slotted wing channel and the upper surface of the wing profile form an included angle, the lower boundary line of the front side boundary of the slotted wing channel and the lower surface of the wing profile form an included angle, and the upper boundary line of the front side boundary of the slotted wing channel and the lower boundary line of the front side boundary of the slotted wing channel intersect at a point C2; thus, the slotted-gate leading-side boundary is made up of the upper boundary line A2C2 of the slotted-gate leading-side boundary and the lower boundary line C2B2 of the slotted-gate leading-side boundary;
the intersection point of the rear boundary of the slat opening slot and the upper surface of the wing profile is a slot opening A1; the intersection point of the rear boundary of the slat opening slot and the lower surface of the wing profile is a slot opening B1; the upper boundary line of the rear side boundary of the slat opening slot way and the upper surface of the wing profile form an included angle, the lower boundary line of the rear side boundary of the slat opening slot way and the lower surface of the wing profile form an included angle, and the upper boundary line of the rear side boundary of the slat opening slot way and the lower boundary line of the rear side boundary of the slat opening slot way intersect at a point C1; thus, the slotted throat rear boundary consists of the upper boundary line A1C1 of the slotted throat rear boundary and the lower boundary line C1B1 of the slotted throat rear boundary;
the third step: and (5) trimming the seam.
And the positions of a seam opening A1, a seam opening B1 and a seam opening B2 are rounded and trimmed aiming at a C1 point and a C2 point in the seam.
The shape modification mode is as follows:
rounding, removing and modifying C1 points and C2 points in the seam, wherein the radius of the removed rounding is 0.07C;
performing rounding removal and shape modification treatment on the seam openings A1 and B1, wherein the radius range of the removed rounding is 0.02 c;
rounding off and modifying the seam opening B2, wherein the radius of the removed rounding is 0.065 c;
the slotted wing after the slot trimming is shown in fig. 6.
The fourth step: and designing a flow deflector.
And performing second rounding shape modification treatment on the slotting position, namely the position of a slot opening A1, on the rear part of the slat-opening airfoil, wherein the radius of the inscribed circle is 0.105c, and the rounding after cutting forms the flow deflector, as shown in FIG. 7.
The fifth step: the guide vane translates.
The guide vane is moved upwards along the normal direction of the local lower surface of the thickest position of the guide vane, the moving range is 0.025c, as shown in fig. 8, finally a layout of increasing the guide vane at the slit passage opening is formed, namely a slit guide vane type high lift device.
According to the following experimental effect example, aiming at the NACA4421 airfoil profile, the slotted guide vane type high lift device provided by the invention is adopted, and the aerodynamic characteristic advantages of the airfoil profile are verified through airfoil profile aerodynamic analysis software:
for a NACA4421 basic airfoil (non-slotted configuration), a slotted configuration (non-installed guide vane) and a slotted guide vane configuration (configuration provided by the invention), aerodynamic characteristics of the three configurations are evaluated by adopting airfoil aerodynamic analysis software. Calculating the state: mach number 0.15, Reynolds number 2X 106. The results of the calculations for the three configurations are compared in table 1.
TABLE 1 comparison of Performance based on three configurations of NACA4421 airfoils
| Airfoil configuration state | Coefficient of maximum lift | Lift-to-drag ratio (stall angle of attack) | Stall angle of attack |
| Un-slotted configuration | 1.32 | 32.2 | 15° |
| Slotting (without installing flow deflector) | 1.82 | 33.1 | 19° |
| Slotted + deflector configuration | 2.32 | 33.7 | 24° |
It can be seen from table 1 that the maximum lift coefficient of the slotted vane configuration is increased by 75.8% compared with that of the basic airfoil (non-slotted configuration), the stall angle of attack is increased by 9 °, and in addition, the corresponding lift-drag ratio at the stall angle of attack is also increased by a small amount. Thus, the slotted vane configuration significantly improves the maximum lift coefficient and stall angle of attack of the airfoil over the base airfoil (un-slotted configuration).
The maximum lift coefficient of the slotted guide vane configuration is increased by 27.5 percent compared with the maximum lift coefficient of the slotted guide vane configuration (without the guide vane), the stall angle of attack is increased by 5 degrees, and in addition, the corresponding lift-drag ratio of the stall angle of attack is also increased by a small margin. Thus, the slotted vane configuration significantly improves the maximum lift coefficient and stall angle of attack of the airfoil over a slotted (no vane mounted) configuration.
According to the slotted guide vane type high lift device provided by the invention, the shape modification treatment is carried out on the slot, the guide vane is added in the slot, and the slot opening A2 close to the guide vane is not subjected to the inverted shape modification treatment, so that the characteristic of an inflection point is kept.
The foregoing is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, various modifications and improvements can be made without departing from the principle of the present invention, and such modifications and improvements should also be considered within the scope of the present invention.
Claims (3)
1. A slotted guide vane type high lift device is characterized in that slots are formed in the upper surface and the lower surface of an airfoil, wherein the slotted range of the upper surface of the airfoil is within 0.15c after the maximum thickness position of the airfoil, and the slotted range of the lower surface of the airfoil is within 0.15c before the maximum thickness position of the airfoil; c is the chord length of the airfoil; the width range of the seam is 0.01 c-0.2 c; the central line of the seam channel inclines to the trailing edge of the airfoil, and the included angle between the central line of the seam channel and the upper surface of the airfoil ranges from 10 degrees to 50 degrees and the included angle between the central line of the seam channel and the lower surface of the airfoil ranges from 50 degrees to 90 degrees;
the boundaries of two sides of the slot way along the front and back directions are the boundary of the front side of the slotted wing slot way and the boundary of the back side of the slotted slat slot way respectively; the intersection point of the front boundary of the slat opening slot and the upper surface of the wing profile is a slot opening A2; the intersection point of the front boundary of the slat opening slot and the lower surface of the airfoil profile is a slot opening B2; the upper boundary line of the front side boundary of the slotted wing channel and the upper surface of the wing profile form an included angle, the lower boundary line of the front side boundary of the slotted wing channel and the lower surface of the wing profile form an included angle, and the upper boundary line of the front side boundary of the slotted wing channel and the lower boundary line of the front side boundary of the slotted wing channel intersect at a point C2; thus, the slotted-gate leading-side boundary is made up of the upper boundary line A2C2 of the slotted-gate leading-side boundary and the lower boundary line C2B2 of the slotted-gate leading-side boundary;
the intersection point of the rear boundary of the slat opening slot and the upper surface of the wing profile is a slot opening A1; the intersection point of the rear boundary of the slat opening slot and the lower surface of the wing profile is a slot opening B1; the upper boundary line of the rear side boundary of the slat opening slot way and the upper surface of the wing profile form an included angle, the lower boundary line of the rear side boundary of the slat opening slot way and the lower surface of the wing profile form an included angle, and the upper boundary line of the rear side boundary of the slat opening slot way and the lower boundary line of the rear side boundary of the slat opening slot way intersect at a point C1; thus, the slotted throat rear boundary consists of the upper boundary line A1C1 of the slotted throat rear boundary and the lower boundary line C1B1 of the slotted throat rear boundary;
performing rounding and shape modification treatment on a seam opening A1, a seam opening B1 and a point C1, a seam opening B2 and a point C2 to obtain a seam wing shape after seam modification;
then, performing second rounding shape modification treatment at the position of the slot on the rear part of the wing profile of the slot wing, namely the position of a slot opening A1, wherein the radius range of an inscribed circle is 0.05 c-0.4 c, and the rounding after cutting forms a flow deflector;
and (3) moving the guide vane upwards along the normal direction of the local lower surface of the thickest position of the guide vane within the moving range of 0.005 c-0.2 c to finally form the layout of increasing the guide vane at the slit opening, thus obtaining the slit guide vane type high lift device.
2. The slotted guide vane type high lift device according to claim 1, wherein rounding and shaping treatment is carried out on a slotted opening A1, a slotted opening B1, a slotted opening C1 point, a slotted opening B2 and a slotted opening C2 point, and specifically comprises the following steps:
c1 point is rounded off and modified, the radius of the removed rounded off is 0.01C-0.3C;
c2 point is rounded and supplemented with shape, the radius of added rounding is 0.01C-0.3C;
the seam road opening A1 is subjected to rounding removal and shape modification treatment, and the radius of the removed rounding is 0.01 c-0.1 c;
rounding, removing and modifying the seam crossing B1, wherein the radius of the removed rounding is 0.01 c-0.1 c;
and rounding, removing and modifying the seam opening B2, wherein the radius of the removed rounding is 0.01 c-0.2 c.
3. The slotted vane type high lift device of claim 1, wherein said slotted vane type high lift device is adapted for use with airfoils having a thickness of 0.12c or more.
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