CN103821801A - Resistance reducing rib - Google Patents
Resistance reducing rib Download PDFInfo
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- CN103821801A CN103821801A CN201410061037.5A CN201410061037A CN103821801A CN 103821801 A CN103821801 A CN 103821801A CN 201410061037 A CN201410061037 A CN 201410061037A CN 103821801 A CN103821801 A CN 103821801A
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- rib
- drag reduction
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- body surface
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Abstract
The invention provides a novel resistance reducing rib. According to the resistance reducing rib, a cutting edge rib is additionally arranged at the position of a sharp corner of the peak of a traditional rib, the advantages, of the cutting edge rib, of being high in resistance reduction performance and free of the influence of a machining round corner are combined, the machining difficulty is considered, and the structural strength is improved. By reasonably selecting the size parameters, such as the height of the rib, the included angle, the thickness of the cutting edge and the height of the cutting edge, of the cross section of the rub, influencing the flowing structure of a boundary layer, increasing the thickness of a viscous bottom layer and limiting the extension movement of streamwise vortices, the purpose of resistance reduction is achieved, the friction resistance on the surfaces of aircrafts, underwater vehicles and ground transportation vehicles is reduced, and the application prospect is broad.
Description
Technical field
The present invention relates to a kind of improved drag reduction by riblets device, reach to change boundary layer flow the effect that reduces frictional resistance by being applied to stream body surface, can be applicable to the fields such as the interior stream of Aeronautics and Astronautics, navigation, traffic above-ground and pipeline.
Background technique
Rib Technology origin is in shark placoid scale rib structure, and this biomimetic features is proved to have very strong practicability and good drag-reduction effect by a large amount of research work.In prior art, think that the rib with drag reduction effect must have sharp keen peak ridge and spacing and low speed striation widths and have certain relation, that is, work as h
+≤ 25 and s
+≤ 30(
see Fig. 1, h is rib heights, and s is rib spacing, and υ is kinematical viscosity, u
τfriction velocity, τ
wbe wall shearing stress, ρ is flowing medium density, and subscript "+" represents with the parameter of wall unit's nondimensionalization, lower with) time there is property of reduction drag, s
+=h
+=15, it is 8% that drag reduction reaches maximum value.Testing what can find to have best property of reduction drag by the rib to different cross section (comprising triangle, rectangle, V-arrangement, semicircle etc.) is triangle section rib.Tooth shape, V font and trapezoidal rib (see figure 1) are tested to contrast, show that tooth shape has the highest drag reduction efficiency, can drag reduction 9.9%, be secondly trapezoidal rib, drag reduction 8.2%, V font only has 5.1%.
Traditional triangle cross section drag reduction by riblets effect is limited and be subject to the impact of peak ridge fillet, though sword type rib drag-reduction effect is more excellent, be not subject to the impact of rib point processing fillet, but thickness thin rib (t=0.02s) like this is difficult to processing, structural strength is not good, destructible in practical application.Above-mentioned rib structure of the prior art has seriously limited the practical application of drag reduction by riblets technology.
Summary of the invention
Consider the advantages and disadvantages part of prior art, the present invention proposes a kind of new drag reduction rib, its innovation is the advantage in conjunction with traditional triangle rib stability aspect, with the outstanding resistance reducing performance of blade rib and the advantage that not affected by rib sharp apex fillet, at triangle section rib point, place increases by one section of blade rib, high in conjunction with blade type drag reduction by riblets performance, do not processed the advantage that fillet affects, also consider difficulty of processing, guarantee the factor of structural strength, rib structure is streamed to body surface (as wing etc.) by reasonable manner following current to being arranged in, by the dimensional parameters (rib heights in choose reasonable rib cross section, angle, thickness of knife edge, height etc.), and then affect boundary layer flow structure and (increase viscous sublayer thickness, restriction flows to the exhibition in whirlpool to motion), strengthen its drag-reduction effect.
The technical solution adopted for the present invention to solve the technical problems: a kind of drag reduction rib structure, comprise substrate, rib crest and rib trough, following current is streamed body surface to being arranged in, it is characterized in that, described in adjacent two, the peak-to-peak space segment of rib ripple forms rib trough, described in each, rib crest comprises two side and a top boss, described top boss is a columnar protrusions upwards stretching perpendicular to base plane along the summit edge line of described two side, the top of this columnar protrusions is a plane, the angle of described two side and described base plane is basic identical, the cross section of described columnar protrusions is substantially rectangular, the setting party of described rib crest and rib trough is to basic identical with the described flow direction that streams body surface, and rib distance s and rib heights h with described in stream body surface the vortex structure yardstick that flows to be same magnitude substantially, wherein, described rib distance s refer to adjacent two described in the peak-to-peak distance of rib ripple, described rib heights h refers to the distance the top planes from described base plane to described top boss.
Preferably, the summit edge line of described top boss can be processed with knuckle or transition chamfering.
Preferably, the bottom surface of described rib trough is flat structures.
Preferably, described rib trough is V-structure.
Preferably, described in each, the angle between the two side of rib crest is about 60 °.
Preferably, the angle between the two side of described rib trough is about 60 °.
Preferably, described rib distance s and rib heights h and wall flow, to the same magnitude of vortex structure yardstick, are generally about 15 wall units.Preferably, the thickness t of described top boss is generally about 0.3 wall unit.
Preferably, the height of described top boss and the ratio of rib heights are about 0.1-0.5.
Preferably, drag reduction rib structure of the present invention, can be applicable to airframe, wing, wing flap etc.
Preferably, drag reduction rib structure of the present invention, can be applicable to hull, submarine etc.
Preferably, drag reduction rib structure of the present invention, can be applicable to the internal surface of fluid line.
Preferably, drag reduction rib structure of the present invention, can and stream body surface by bonding mode and connect firmly.
Preferably, drag reduction rib structure of the present invention, can be by forming in the mode of streaming the direct processing of body surface.
Wall unit of the present invention is υ/u
τ, wherein: υ is flowing medium kinematical viscosity,
be friction velocity, ρ is flowing medium density, τ
wit is wall shearing stress.
Drag reduction rib structure of the present invention is a kind of novel drag reduction by riblets technology, have advantages of outstanding than traditional drag reduction rib structure: the advantage that combines the advantage of traditional triangle rib stability aspect and the outstanding resistance reducing performance of blade rib and not affected by rib sharp apex fillet, at triangle section rib point, place increases by one section of blade rib, high in conjunction with blade type drag reduction by riblets performance, do not processed the advantage that fillet affects, also consider difficulty of processing, guarantee the factor of structural strength, rib structure is streamed to body surface (as wing etc.) by reasonable manner following current to being arranged in, by the dimensional parameters (rib heights in choose reasonable rib cross section, angle, thickness of knife edge, height etc.), and then affect boundary layer flow structure and (increase viscous sublayer thickness, restriction flows to the exhibition in whirlpool to motion), strengthen its drag-reduction effect.
Accompanying drawing explanation
Fig. 1 is conventional rib schematic cross-section, and wherein Fig. 1 a is the conventional rib in V-arrangement cross section, the conventional rib that Fig. 1 b is trapezoid cross section, and Fig. 1 c is the conventional rib in tooth shape cross section;
Fig. 2 is the schematic cross-section of drag reduction rib structure of the present invention perpendicular to the flow direction, and its rib trough is V-structure;
Fig. 3 is the schematic cross-section of drag reduction rib structure of the present invention perpendicular to the flow direction, and the bottom surface of its rib trough is flat structures;
Fig. 4 is the axonometric drawing of drag reduction rib structure of the present invention, and its rib trough is V-structure;
Fig. 5 is the axonometric drawing of drag reduction rib structure of the present invention, and the bottom surface of its rib trough is flat structures;
Fig. 6 is that drag reduction rib structure of the present invention adheres to the schematic diagram that streams body surface.
Embodiment
Below in conjunction with embodiment, the present invention is described in further detail, and following examples are explanation of the invention and the present invention is not limited to following examples.
As shown in Figures 2 to 5, drag reduction rib structure of the present invention, comprise substrate 1, rib crest 2 and rib trough 3, following current is streamed body surface to being arranged in, space segment described in adjacent two between rib crest 1 forms rib trough 2, described in each, rib crest 1 comprises two side 11 and a top boss 12, described top boss 12 is the columnar protrusions that a summit edge line along described two side 11 upwards stretches perpendicular to base plane 1, the top of this columnar protrusions is a plane, described two side 11 is basic identical with the angle of described base plane 1, the cross section of described columnar protrusions is substantially rectangular, the setting party of described rib crest 2 and rib trough 3 is to basic identical with the described flow direction that streams body surface, and rib distance s and rib heights h with described in stream body surface the vortex structure yardstick that flows to be same magnitude substantially, wherein, described rib distance s refers to the distance between rib crest 2 described in adjacent two, and described rib heights h refers to from described base plane 1 to the distance the top planes of described top boss 12.
Preferably, the summit edge line of described top boss 12 can be processed with knuckle or transition chamfering.Preferably, the bottom surface of described rib trough 3 is flat structures or V-structure.
Preferably, described in each, the angle between the two side of rib crest is about 60 °.Preferably, the angle between the two side of described rib trough is about 60 °.
Preferably, described rib distance s and rib heights h and wall flow, to the same magnitude of vortex structure yardstick, are generally about 15 wall units.Preferably, the thickness t of described top boss is generally about 0.3 wall unit.Preferably, the ratio of the height of described top boss and rib heights h is about 0.1-0.5.
Preferably, drag reduction rib structure of the present invention, can be applicable to airframe, wing, wing flap etc., or is applied to hull, submarine etc., or be applied to the internal surface of fluid line.Preferably, drag reduction rib structure of the present invention, can and stream body surface by bonding mode and connect firmly, or by forming in the mode of streaming the direct processing of body surface.
As shown in Figure 6, drag reduction rib structure of the present invention can be made fexible film and adheres to and stream body surface.Airflow passes stream the following current of arranging on body surface to rib, because rib structure has increased the thickness of boundary layer viscous sublayer, reduce the average velocity gradient on wall, rib spike has hindered the generation of the instantaneous lateral flow being caused by turbulent motion, weaken transporting of wall turbulence momentum, the surface friction drag of rib surface is reduced.
In addition, it should be noted that, the specific embodiment described in this specification, shape, institute's title of being named etc. of its parts and components can be different.All equivalence or simple change of doing according to described structure, feature and the principle of patent design of the present invention, are included in the protection domain of patent of the present invention.Those skilled in the art can make various modifications or supplement or adopt similar mode to substitute described specific embodiment; only otherwise depart from structure of the present invention or surmount this scope as defined in the claims, all should belong to protection scope of the present invention.
Claims (10)
1. a drag reduction rib structure, comprise substrate, rib crest and rib trough, following current is streamed body surface to being arranged in, it is characterized in that, described in adjacent two, the peak-to-peak space segment of rib ripple forms rib trough, described in each, rib crest comprises two side and a top boss, described top boss is a columnar protrusions upwards stretching perpendicular to base plane along the summit edge line of described two side, the top of this columnar protrusions is a plane, the angle of described two side and described base plane is basic identical, and the cross section of described columnar protrusions is substantially rectangular; The setting party of described rib crest and rib trough is to basic identical with the described flow direction that streams body surface, and rib distance s and rib heights h with described in stream body surface the vortex structure yardstick that flows to be same magnitude substantially, wherein, described rib distance s refer to adjacent two described in the peak-to-peak distance of rib ripple, described rib heights h refers to the distance the top planes from described base plane to described top boss.
2. drag reduction rib structure according to claim 1, is characterized in that, the summit edge line of described top boss can be processed with knuckle or transition chamfering.
3. drag reduction rib structure according to claim 1, is characterized in that, the bottom surface of described rib trough is flat structures.
4. drag reduction rib structure according to claim 1, is characterized in that, described rib trough is V-structure.
5. according to the drag reduction rib structure described in claim 1 to 4, it is characterized in that, the angle described in each between the two side of rib crest is about 60 °.
6. according to the drag reduction rib structure described in claim 1 to 5, it is characterized in that, the angle between the two side of described rib trough is about 60 °.
7. according to the drag reduction rib structure described in claim 1 to 5, it is characterized in that, described rib distance s and rib heights h and wall flow are to the same magnitude of vortex structure yardstick, generally be about 15 wall units, the thickness t of described top boss is generally about 0.3 wall unit, wherein: described wall unit is υ/u
τ, υ is flowing medium kinematical viscosity,
be friction velocity, ρ is flowing medium density, τ
wit is wall shearing stress.
8. according to the drag reduction rib structure described in claim 1 to 5, it is characterized in that, the height of described top boss and the ratio of rib heights are about 0.1-0.5.
9. according to the drag reduction rib structure described in claim 1 to 5, it is characterized in that, can and stream body surface by bonding mode and connect firmly, maybe can be by forming in the mode of streaming the direct processing of body surface.
10. according to the drag reduction rib structure described in claim 1 to 5, it is characterized in that, described drag reduction rib structure, can be applicable to airframe, wing, wing flap etc., or hull, submarine etc., or the internal surface of fluid line.
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Cited By (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN105644770A (en) * | 2015-12-30 | 2016-06-08 | 哈尔滨工业大学 | Sharkskin-imitating resistance-reducing wing |
CN108999846A (en) * | 2018-08-14 | 2018-12-14 | 中国科学院工程热物理研究所 | A kind of super-hydrophobic drag reduction rib structure |
CN110939712A (en) * | 2019-12-17 | 2020-03-31 | 合肥工业大学 | Shark bionic gear |
CN111336162A (en) * | 2020-03-25 | 2020-06-26 | 中国科学院国家空间科学中心 | Device for converting space directional flow direction to balanced flow |
WO2020151379A1 (en) * | 2019-01-24 | 2020-07-30 | 深圳大学 | Unmanned aerial vehicle rotor surface microstructure drag-reducing film and manufacturing method thereof |
CN111611661A (en) * | 2020-05-26 | 2020-09-01 | 北京航空航天大学 | Transverse V-shaped groove structure based on stable vortex string resistance reduction and application thereof |
CN112548359A (en) * | 2020-11-30 | 2021-03-26 | 贵州大学 | Preparation method of surface functional composite structured monocrystalline silicon carbide |
CN113665728A (en) * | 2021-09-14 | 2021-11-19 | 中国海洋大学 | Bionic drag reduction method for underwater vehicle and water surface ship |
CN115258033A (en) * | 2022-08-03 | 2022-11-01 | 青岛科技大学 | Micro-groove bionic drag reduction structure and preparation method thereof |
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CN101758864A (en) * | 2010-01-14 | 2010-06-30 | 浙江大学 | Bionic non-smooth surface film with pneumatic drag reduction effect |
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CN102886923A (en) * | 2012-10-23 | 2013-01-23 | 吉林大学 | Coupling bionic structure for improving erosion resistance of mechanical moving part surface |
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CN103498838A (en) * | 2013-10-11 | 2014-01-08 | 吉林大学 | Bionic resistance-reducing noise-reducing surface of rigid and flexible structure |
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CN101109402A (en) * | 2006-07-19 | 2008-01-23 | 北京航空航天大学 | Rib strip-tiny bubble damping device |
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CN101758864A (en) * | 2010-01-14 | 2010-06-30 | 浙江大学 | Bionic non-smooth surface film with pneumatic drag reduction effect |
CN102803750A (en) * | 2010-02-10 | 2012-11-28 | 蒂森克虏伯钢铁欧洲股份公司 | Product for fluidic applications, method for the production thereof, and use of such a product |
KR20120140615A (en) * | 2011-06-21 | 2012-12-31 | 첸-신 메이 | The method of reducing resistance of streamlined body of a vehicle and its applications |
KR20130123126A (en) * | 2012-05-02 | 2013-11-12 | 한국철도기술연구원 | Device for variable dimple type reducing the aerodynamic drag of high speed train |
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Cited By (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN105644770A (en) * | 2015-12-30 | 2016-06-08 | 哈尔滨工业大学 | Sharkskin-imitating resistance-reducing wing |
CN108999846A (en) * | 2018-08-14 | 2018-12-14 | 中国科学院工程热物理研究所 | A kind of super-hydrophobic drag reduction rib structure |
CN108999846B (en) * | 2018-08-14 | 2023-09-19 | 中国科学院工程热物理研究所 | Super-hydrophobic drag reduction rib structure |
WO2020151379A1 (en) * | 2019-01-24 | 2020-07-30 | 深圳大学 | Unmanned aerial vehicle rotor surface microstructure drag-reducing film and manufacturing method thereof |
CN110939712A (en) * | 2019-12-17 | 2020-03-31 | 合肥工业大学 | Shark bionic gear |
CN111336162A (en) * | 2020-03-25 | 2020-06-26 | 中国科学院国家空间科学中心 | Device for converting space directional flow direction to balanced flow |
CN111611661A (en) * | 2020-05-26 | 2020-09-01 | 北京航空航天大学 | Transverse V-shaped groove structure based on stable vortex string resistance reduction and application thereof |
CN112548359A (en) * | 2020-11-30 | 2021-03-26 | 贵州大学 | Preparation method of surface functional composite structured monocrystalline silicon carbide |
CN113665728A (en) * | 2021-09-14 | 2021-11-19 | 中国海洋大学 | Bionic drag reduction method for underwater vehicle and water surface ship |
CN115258033A (en) * | 2022-08-03 | 2022-11-01 | 青岛科技大学 | Micro-groove bionic drag reduction structure and preparation method thereof |
CN115258033B (en) * | 2022-08-03 | 2023-09-15 | 青岛科技大学 | Micro-groove bionic drag reduction structure and preparation method thereof |
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