CN112733278A - Passive delay turbulence transition control device and method - Google Patents
Passive delay turbulence transition control device and method Download PDFInfo
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- CN112733278A CN112733278A CN202110347545.XA CN202110347545A CN112733278A CN 112733278 A CN112733278 A CN 112733278A CN 202110347545 A CN202110347545 A CN 202110347545A CN 112733278 A CN112733278 A CN 112733278A
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Abstract
The invention belongs to the technical field of transition control of turbulence flow, and particularly relates to a control device and method for passively delaying transition of turbulence flow. The technical scheme is as follows: the utility model provides a passive delay turbulent flow transition control device of twining, includes the cone, is provided with the coarse unit that is used for weakening the vortex of flow direction under big attack angle operating mode on the cone, and coarse unit protrusion is on the cone surface. The invention provides a control device and method for passively delaying transition of turbulence to reduce resistance of an aircraft.
Description
Technical Field
The invention belongs to the technical field of transition control of turbulence flow, and particularly relates to a control device and method for passively delaying transition of turbulence flow.
Background
The transition from laminar flow to turbulent flow has great influence on the friction resistance and the thermal load of the hypersonic aircraft. Therefore, it is important to understand the transition phenomenon and mechanism from laminar flow to turbulent flow for aircraft design. For the stability of the hypersonic velocity boundary layer and transition characteristics such as flat plate and conical flow, a great deal of research has been carried out through experiments and theoretical analysis, and a clear understanding is obtained, as shown in fig. 3. Fig. 3 shows that the coefficient of friction of the hypersonic conical wall surface sharply increases after the occurrence of the turbulence transition.
For hypersonic aircraft, a cone is a typical nominal mode profile, while a cone with an angle of attack is a typical hypersonic three-dimensional boundary layer flow. Fig. 4 shows a typical turbulent transition flow characteristic with an angle of attack cone. That is, the main transition of the constant cross flow vortex occurs on the side surface of the cone, and the main transition of the flow vortex occurs on the top of the cone leeward region. Wherein the thickness of the steady cross flow vortex is the order of the thickness scale of the boundary layer, and the thickness of the top middle flow vortex is the thickness of several or even more than ten boundary layers.
The passive turbulence transition control technology mainly refers to a control technology without energy consumption, and the most of the control technology is to change and increase a rough unit in the turbulence transition control process of the aircraft. For the turbulent transition flow of the high supersonic speed large attack angle conical side surface region, the transition flow is dominated by constant cross flow vortex (steady cross flow vortex) as shown in fig. 4. For transition of high-attack-angle side turbulence, it is proved that the transition process dominated by constant cross flow vortex can be effectively controlled by adopting a micro-scale coarse unit. The method is that a circle of micro-scale rough units are arranged on the surface near the front edge of the cone along the circumferential direction, as shown in figure 5. Fig. 6 shows an enlarged detail view of the cone circumferentially distributed coarse cells, which are in a concave structure. Wherein the height of the coarse cells is in the mum order of magnitude. For the hypersonic velocity band attack angle conical flow, a circle of coarse units are circumferentially arranged near the front edge, so that transition of a constant transverse flow vortex dominant transition of a conical side flow area can be effectively inhibited. The mechanism is that the steady cross flow disturbance is excited by the wall surface roughness of the front edge of the cone, and a circle of equally spaced coarse units are arranged near the front edge of the cone, so that the secondary unstable steady cross flow disturbance is excited, and the most unstable steady cross flow disturbance is inhibited, thereby achieving the purpose of delayed transition.
However, for the flow of the hypersonic large-attack-angle cone top leeward region, the flow direction vortex is generated by flow separation, the size of the flow direction vortex is larger, and the micro-scale rough unit has almost no influence on the stability of the flow direction vortex. Therefore, the micro-scale rough unit has little effect on delaying the transition of turbulence to the vortex.
Disclosure of Invention
In order to solve the above problems in the prior art, the present invention provides a control device and method for delaying transition of a turbulent flow to reduce the resistance of an aircraft.
The technical scheme adopted by the invention is as follows:
the utility model provides a passive delay turbulent flow transition control device of twining, includes the cone, is provided with the coarse unit that is used for weakening the vortex of flow direction under big attack angle operating mode on the cone, and coarse unit protrusion is on the cone surface.
The large-scale coarse cells are arranged near the cone leading edge and only 1 is arranged.
Aiming at the flow direction vortex flow of the top of the hypersonic large-attack-angle cone leeward starting part, the rough unit can be used for delaying the transition of the flow direction vortex flow of the top of the hypersonic large-attack-angle cone leeward area. The rough unit can weaken the strength of the flow vortex, weaken the instability of the rough unit, achieve the effect of inhibiting the transition of the turbulence, and play the role of delaying the transition of the turbulence and reducing the resistance of the aircraft. The coarse cell arrangement of the present invention is a passive control technique that does not require active energy consumption.
In a preferred embodiment of the present invention, the shape of the roughness elements is a mountain peak shape.
As a preferable scheme of the invention, the distance between the coarse unit and the tip of the cone is 20-80 mm. Wherein, the distance specifically refers to the distance between the highest point of the coarse unit and the tip of the cone.
As a preferable scheme of the invention, the width of the coarse unit in the direction vertical to the central line of the cone is 0.8-1.6 mm. Wherein, the calculation starting and stopping points of the width are all the tangent points of the cambered surface of the rough unit and the surface of the conical body.
In a preferred embodiment of the present invention, the height of the roughness elements is 0.6 to 1.2 mm. The height of the coarse cell refers to the distance between the highest point of the coarse cell and the centerline of the cone minus the radius of the cone.
As a preferable scheme of the invention, the distance between the coarse unit and the bottom of the cone is 400-480 mm. The distance between the coarse unit and the bottom of the cone refers to the projection distance of the connecting line of the highest point of the coarse unit and the bottom of the cone on the center line of the cone.
A passive delay turbulence transition control method comprises the following steps:
the cone is provided with a rough unit for weakening flow direction vortex under the working condition of a large attack angle, so that the rough unit protrudes out of the surface of the cone.
In a preferred embodiment of the present invention, the shape of the roughness elements is a mountain peak shape.
As a preferable scheme of the invention, the distance between the coarse unit and the tip of the cone is 20-80 mm. Wherein, the distance specifically refers to the distance between the highest point of the coarse unit and the tip of the cone.
As a preferable scheme of the invention, the width of the coarse unit in the direction vertical to the central line of the cone is 0.8-1.6 mm; the height of the coarse unit is 0.6-1.2 mm. Wherein, the calculation starting and stopping points of the width are all the tangent points of the cambered surface of the rough unit and the surface of the conical body. The height of the coarse cell refers to the distance between the highest point of the coarse cell and the centerline of the cone minus the radius of the cone.
The invention has the beneficial effects that:
aiming at the flow direction vortex flow at the top of the hypersonic-speed large-attack-angle cone leeward starting part, the rough unit can be used for delaying the flow direction vortex flow transition at the top of the hypersonic-speed large-attack-angle cone leeward area. The rough unit can weaken the strength of the flow vortex, weaken the instability of the rough unit, achieve the effect of inhibiting the transition of the turbulence, and play the role of delaying the transition of the turbulence and reducing the resistance of the aircraft. The coarse cell arrangement of the present invention is a passive control technique that does not require active energy consumption.
Drawings
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is a partial block diagram of the present invention;
FIG. 3 is a graph of friction coefficient during a transition of a hypersonic conical surface;
FIG. 4 is a diagram of typical flow characteristics of a hypersonic cone with angle of attack;
FIG. 5 is a diagram of hypersonic cone leading edge roughness cells with angles of attack;
fig. 6 is a partially enlarged view of a portion a in fig. 5.
In the figure, 1-cone; 2-coarse cells.
Detailed Description
Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention.
As shown in fig. 1 and fig. 2, the passive delay turbulence transition control device of the present embodiment includes a cone 1, a rough unit 2 for weakening a flow vortex under a large attack angle condition is arranged on the cone 1, and the rough unit 2 protrudes out of the surface of the cone 1. The large-scale coarse cells 2 are arranged near the cone leading edge, and only 1 is arranged.
Aiming at the flow transition of the top flow direction vortex of the hypersonic large-attack-angle cone leeward wake, the rough unit 2 can be used for delaying the flow transition of the top flow direction vortex of the hypersonic large-attack-angle cone leeward wake. The rough unit 2 can weaken the strength of flow direction vortexes, weaken the instability of the vortex and achieve the effect of inhibiting the transition of turbulence, and play a role in delaying the transition of the turbulence and reducing the resistance of the aircraft. The arrangement of the coarse cells 2 of the invention is a passive control technique, without the need for active energy consumption.
Wherein, the height of the coarse unit 2 is 0.6-1.2 mm. The shape of the roughness elements 2 is a mountain shape. The large-scale rough unit 2 is in a peak shape, the height of the large-scale rough unit can be changed along with the working condition of incoming flow, and under the condition of high supersonic speed, the height of the large-scale rough unit 2 is generally set to be 1 cm.
The distance between the coarse unit 2 and the tip of the cone 1 is 20-80 mm, and can be set to 60 mm.
The width of the coarse unit 2 in the direction perpendicular to the central line of the cone 1 is 0.8-1.6 mm, and is usually set to be 1.2 mm. The roughness elements 2 may be symmetrically arranged so that the distance from the center line of the roughness elements 2 to one side is 0.6 mm.
The distance between the coarse unit 2 and the bottom of the cone 1 is 400-480 mm, and is usually 440 mm.
A passive delay turbulence transition control method comprises the following steps:
a rough unit 2 for weakening flow direction vortex under the working condition of a large attack angle is arranged on the cone 1, and the rough unit 2 protrudes out of the surface of the cone 1.
Wherein the shape of the coarse unit 2 is a mountain peak shape. The distance between the rough unit 2 and the tip of the cone 1 is 20-80 mm. The width of the coarse unit 2 in the direction vertical to the central line of the cone 1 is 0.8-1.6 mm; the height of the coarse unit 2 is 0.6-1.2 mm.
The invention is not limited to the above alternative embodiments, and any other various forms of products can be obtained by anyone in the light of the present invention, but any changes in shape or structure thereof, which fall within the scope of the present invention as defined in the claims, fall within the scope of the present invention.
Claims (10)
1. The utility model provides a control device is twisted to passive delay torrent circulation, its characterized in that includes cone (1), is provided with on cone (1) to be used for weakening coarse unit (2) at the big angle of attack operating mode's that flow direction whirlpool, and coarse unit (2) protrusion is on cone (1) surface.
2. A passive delay turbulence transition control apparatus according to claim 1, characterized in that the shape of the rough unit (2) is a mountain peak shape.
3. The control device for transition of passive delay turbulence in accordance with claim 1, characterized in that the distance between the rough unit (2) and the tip of the cone (1) is 20-80 mm.
4. The apparatus for controlling transition of passive delay turbulence in accordance with claim 1, wherein the width of the roughness element (2) in the direction perpendicular to the center line of the cone (1) is 0.8-1.6 mm.
5. The apparatus for controlling transition of passive delay turbulence in accordance with claim 1, wherein the height of the roughness element (2) is 0.6-1.2 mm.
6. The apparatus for controlling transition of passive delay turbulence in accordance with claim 1, wherein the distance between the rough unit (2) and the bottom of the cone (1) is 400-480 mm.
7. A control method for passively delaying transition of turbulence is characterized by comprising the following steps:
the cone (1) is provided with a rough unit (2) for weakening flow direction vortex under the working condition of a large attack angle, so that the rough unit (2) protrudes out of the surface of the cone (1).
8. The control method for transition of passive delay turbulence in accordance with claim 7, characterized in that the shape of the coarse unit (2) is mountain peak shape.
9. The control method of transition of passive delay turbulence in accordance with claim 7, characterized in that the distance between the rough unit (2) and the tip of the cone (1) is 20-80 mm.
10. The control method for transition of passive delay turbulence in accordance with claim 7, wherein the width of the coarse unit (2) in the direction perpendicular to the center line of the cone (1) is 0.8-1.6 mm; the height of the coarse unit (2) is 0.6-1.2 mm.
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113158347A (en) * | 2021-05-17 | 2021-07-23 | 中国空气动力研究与发展中心计算空气动力研究所 | Method for rapidly determining position of flow direction vortex in high-speed three-dimensional boundary layer |
| CN113998145A (en) * | 2022-01-04 | 2022-02-01 | 中国空气动力研究与发展中心计算空气动力研究所 | Method, device, equipment and medium for detecting instability characteristics of aircraft boundary layer |
| CN114441134A (en) * | 2022-01-07 | 2022-05-06 | 中国空气动力研究与发展中心计算空气动力研究所 | Method for inhibiting Mack mode by adopting steady crossflow vortex |
| CN116552777A (en) * | 2023-07-05 | 2023-08-08 | 中国空气动力研究与发展中心计算空气动力研究所 | Vortex regulator and aircraft |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113158347A (en) * | 2021-05-17 | 2021-07-23 | 中国空气动力研究与发展中心计算空气动力研究所 | Method for rapidly determining position of flow direction vortex in high-speed three-dimensional boundary layer |
| CN113998145A (en) * | 2022-01-04 | 2022-02-01 | 中国空气动力研究与发展中心计算空气动力研究所 | Method, device, equipment and medium for detecting instability characteristics of aircraft boundary layer |
| CN114441134A (en) * | 2022-01-07 | 2022-05-06 | 中国空气动力研究与发展中心计算空气动力研究所 | Method for inhibiting Mack mode by adopting steady crossflow vortex |
| CN116552777A (en) * | 2023-07-05 | 2023-08-08 | 中国空气动力研究与发展中心计算空气动力研究所 | Vortex regulator and aircraft |
| CN116552777B (en) * | 2023-07-05 | 2023-09-12 | 中国空气动力研究与发展中心计算空气动力研究所 | Vortex regulator and aircraft |
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