WO2014109670A2 - Method and apparatus for achieving laminar flow of gas or liquid near cutting edges - Google Patents

Method and apparatus for achieving laminar flow of gas or liquid near cutting edges Download PDF

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Publication number
WO2014109670A2
WO2014109670A2 PCT/RU2013/001035 RU2013001035W WO2014109670A2 WO 2014109670 A2 WO2014109670 A2 WO 2014109670A2 RU 2013001035 W RU2013001035 W RU 2013001035W WO 2014109670 A2 WO2014109670 A2 WO 2014109670A2
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WO
WIPO (PCT)
Prior art keywords
point
cutting edge
term
true
aerodynamic
Prior art date
Application number
PCT/RU2013/001035
Other languages
French (fr)
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WO2014109670A3 (en
Inventor
Nikolay Alekseevich TRUBAEV
Original Assignee
Trubaev Nikolay Alekseevich
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
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Priority to PCT/RU2013/001035 priority Critical patent/WO2014109670A2/en
Publication of WO2014109670A2 publication Critical patent/WO2014109670A2/en
Publication of WO2014109670A3 publication Critical patent/WO2014109670A3/en

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C21/00—Influencing air flow over aircraft surfaces by affecting boundary layer flow
    • B64C21/10—Influencing air flow over aircraft surfaces by affecting boundary layer flow using other surface properties, e.g. roughness
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03D—WIND MOTORS
    • F03D1/00—Wind motors with rotation axis substantially parallel to the air flow entering the rotor 
    • F03D1/06—Rotors
    • F03D1/0608—Rotors characterised by their aerodynamic shape
    • F03D1/0633—Rotors characterised by their aerodynamic shape of the blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
    • F15D—FLUID DYNAMICS, i.e. METHODS OR MEANS FOR INFLUENCING THE FLOW OF GASES OR LIQUIDS
    • F15D1/00—Influencing flow of fluids
    • F15D1/10—Influencing flow of fluids around bodies of solid material
    • F15D1/12—Influencing flow of fluids around bodies of solid material by influencing the boundary layer
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
    • B63B—SHIPS OR OTHER WATERBORNE VESSELS; EQUIPMENT FOR SHIPPING 
    • B63B1/00—Hydrodynamic or hydrostatic features of hulls or of hydrofoils
    • B63B1/02—Hydrodynamic or hydrostatic features of hulls or of hydrofoils deriving lift mainly from water displacement
    • B63B1/04—Hydrodynamic or hydrostatic features of hulls or of hydrofoils deriving lift mainly from water displacement with single hull
    • B63B1/06—Shape of fore part
    • B63B1/063—Bulbous bows
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
    • B63B—SHIPS OR OTHER WATERBORNE VESSELS; EQUIPMENT FOR SHIPPING 
    • B63B1/00—Hydrodynamic or hydrostatic features of hulls or of hydrofoils
    • B63B1/32—Other means for varying the inherent hydrodynamic characteristics of hulls
    • B63B1/34—Other means for varying the inherent hydrodynamic characteristics of hulls by reducing surface friction
    • B63B1/36—Other means for varying the inherent hydrodynamic characteristics of hulls by reducing surface friction using mechanical means
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C2230/00—Boundary layer controls
    • B64C2230/26—Boundary layer controls by using rib lets or hydrophobic surfaces
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2250/00—Geometry
    • F05B2250/60—Structure; Surface texture
    • F05B2250/61—Structure; Surface texture corrugated
    • F05B2250/611—Structure; Surface texture corrugated undulated
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
    • Y02E10/00—Energy generation through renewable energy sources
    • Y02E10/70—Wind energy
    • Y02E10/72—Wind turbines with rotation axis in wind direction
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/10—Drag reduction
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T70/00—Maritime or waterways transport
    • Y02T70/10—Measures concerning design or construction of watercraft hulls

Definitions

  • the invention relates to an apparatus for reducing turbulent drag, especially in aircraft and watercraft.
  • the forms of surfaces are described, which delay or prevent boundary layer separation without creating an undesirable drag penalty.
  • These forms jean be used for turbulent drag reduction of surfaces in a flow of gas or liquid, for example, for inner surface of a tube.
  • This invention relates to aerodynamic and hydrodynamic components having leading edge devices for the improvement of performance, for example, for construction of bulbous bows for bulk carriers.
  • aerodynamic and hydrodynamic component is used herein to encompass structures having an airfoil or hydrofoil section and leading edge. This term
  • wings is intended to include wings, fins, tailplanes, canards, engine components such as turbine and compressor blades, propeller blades, helicopter rotor blades, and similar items.
  • the ideal fluid model can be used as model of flow of gas or liquid in some distance from surfaces of solid bodies. Near these surfaces the boundary layer lays,
  • the ideal fluid model has no solutions for nfinite velocity. So the appearance of vortexes and the separation of the boundary layer in these cases are impossible or delayed near the cutting edges. As a result the flow is steady there and the turbulent drag is absent.
  • This effect can be used not only for any edge of construction, but for reducing the turbulent drag on the surfaces of bodies as well. For example, for reducing the turbulent drag on the surfaces of aircraft or watercraft units, or on the inner surface of tube. For this purpose we need to create the shape of these surfaces characterized by an array of spaced cutting edges, near which the separation of the boundary layer is delayed or prevented, so the average value of turbulent drag will be reduced.
  • Fig.l, Fig.2, Fig.3 are three different views of surface, for which the claim 1.1 is true in point P.
  • Fig.4 are surfaces, for which the claim 1.2.1 is true in crossing line between points D and E.
  • Fig.5 are surfaces, for which the claim 1.2 is true. In crossing line between points F, G and between points G, H the claim 1.2.1 is true. In the point G the claim 1.2.2 is true.
  • Fig.6 and Fig.7 are examples of surface, which has array of spaced cutting edges, for which claim 1.2.1 is true.
  • Fig.8 is example of surface, which has array of spaced cutting edges, for which the-claim 2 is true: in any point of cutting edge, where flat elements do not touch, the claim ⁇ .2 ⁇ is true; in points, where flat elements do touch, the claim 1.2.2 s true.
  • Fig.9 is profile of few crossed surfaces, which can be modified for achieving laminarity of flow of gas or liquid near point P as Fig.10, Fig.l 1 show.
  • Fig.10 and Fig.l 1 are two variants of modification of profile Fig.9 for achieving laminarity of flow of gas or liquid near point P, where the claim 1.1 is true.
  • Fig.12 is scheme of bulk carrier with bulbous bow.
  • Fig.13 is prototype of bulbous bow for bulk carrier, in which the claim 1.1 is true in point A, as Fig.l, Fig.2, Fig.3 show, and the claim 2 is true in the region marked by letter C, where it can be used for surfaces such as in Fig 6, Fig.7 arid Fig.8.
  • Fig.14 is scheme of wind power plant.
  • Fig.15 is prototype of the blade of wind power plant, where for the leading and trailing edges the claim 1.2.1 is true. These edges are marked by letter B.
  • Fig.16 and Fig.17 are two views of part of the blade from Fig.15.
  • Fig.18 is scheme of aircraft showing the regions, where the claims of invention can be used: regions marked by letter A are for the use of claim 1.1; regions marked by letter B are for the use of claim 1.2; regions marked by letter C are for the use of claim 2.
  • Fig.19 and Fig.20 are two views of the part of prototype for wing of an aircraft with leading-edge slat, where claim 1.2.1 is true for the leading and trailing edges.
  • the claim 1.1 is true in point P. It can be used, for example, as part of the bulbous bow Fig.13 in point A of bulk carrier shown in Fig.12. In region, marked by letter C in Fig.13, where the initial boundary layer separation is possible, the profiles Fig.6, Fig.7, Fig.8 of surface can be used. For profiles Fig.6, Fig.7 and Fig.8 of surface the claim 2 is true. The average value of turbulent drag reduces near these surfaces.
  • the variant of blade shown in Fig.15, Fig.16 and Fig 17 can be used.
  • the leading and trailing cutting edges of the blade marked by letter B in Fig.15, that are shown in Fig.16 and Fig.17, the claim 1.2.1 is true.
  • This profile with the cutting edge is an alternative to the profile of smooth surface, in which the drag of laminar flow near leading cutting edge is generally lower.
  • the trailing cutting edge for which the claim 1.2 is true, is also preferred to the profile of smooth surface or traditional trailing cutting edge with profile of a wedge, because the appearance of vortex near this cutting edge is delayed or prevented.
  • Fig.18 there is possibility for the use the invention in the regions, marked by letters A, B, C.
  • the claim 1.1 can be used.
  • the variants for this use are shown in Fig.l, Fig.2, Fig.3 and in Fig.10, Fig.l 1 as well.
  • initial profile of surface is shown in Fig.9 .
  • the variant with solitary point as cutting edge is preferred, the achieving of laminarity of flow near some point on the line of cutting edge or the crossing of cutting edges, as shown in Fig.9 in point P, is also possible. In this case
  • claim 2 can be used for reducing the extent of turbulent drag by delaying or preventing the separation of the boundary layer there.
  • Fig.6, Fig.7 and Fig.8 are showing some of possible profiles of such surfaces, for which the claim 2 is true.
  • the profile in Fig.8 is more suitable for places, where the flow can change direction.
  • the claim 2 and surfaces Fig.6, Fig.7, Fig.8 can be used for reducing the turbulent 4rag of the surfaces of tubes or underwater constructions.
  • the best mode for carrying out the invention includes full realization of claims conditions in part of surface near a cutting edge.
  • the best mode is the embodiment of the surface, which touches the cones with different aperture angles in maximum possible number of tangent rays in the point of cutting edge.
  • the best mode is the embodiment, when one of crossing surface is plane.
  • the best mode is the embodiment, where an array of spaced cutting edges lays in the regions, where the initial separation of the boundary layer is possible.

Abstract

The invention relates to an apparatus for reducing turbulent drag, especially in aircraft and watercraft. The forms of surfaces are described, which delay or prevent boundary layer separation without creating an undesirable drag penalty. These forms can be used for turbulent drag reduction of surfaces in a flow of gas or liquid, for example, for inner surface of a tube. This invention relates to aerodynamic and hydrodynamic components having leading edge devices for the improvement of performance, for example, for construction of bulbous bows for bulk carriers. The term "aerodynamic and hydrodynamic component" is used herein to encompass structures having an airfoil or hydrofoil section and leading edge. This term is intended to include wings, fins, tailplanes, canards, engine components such as turbine and compressor blades, propeller blades, helicopter rotor blades, and similar items.

Description

METHOD AND APPARATUS FOR ACHIEVING LAMINAR FLOW OF GAS OR LIQUID NEAR CUTTING EDGES
TECHNICAL FIELD OF THE INVENTION
The invention relates to an apparatus for reducing turbulent drag, especially in aircraft and watercraft. The forms of surfaces are described, which delay or prevent boundary layer separation without creating an undesirable drag penalty. These forms jean be used for turbulent drag reduction of surfaces in a flow of gas or liquid, for example, for inner surface of a tube.
This invention relates to aerodynamic and hydrodynamic components having leading edge devices for the improvement of performance, for example, for construction of bulbous bows for bulk carriers.
The term "aerodynamic and hydrodynamic component" is used herein to encompass structures having an airfoil or hydrofoil section and leading edge. This term
is intended to include wings, fins, tailplanes, canards, engine components such as turbine and compressor blades, propeller blades, helicopter rotor blades, and similar items.
BACKGROUND ART
The ideal fluid model can be used as model of flow of gas or liquid in some distance from surfaces of solid bodies. Near these surfaces the boundary layer lays,
in which the velocity of flow increases from zero to some finite value. In the ideal fluid model near the regions of the cutting edges of boundary the appearance of infinite values of velocity is possible as solutions of differential equation. So in real situations near cutting edges vortexes and separation of the boundary layer in laminar and turbulent parts can appear. The vortexes and the separation of the boundary layer make the flow unstable and turbulent drag appears. Although the Reynolds-number, the Mach-number, and the wall temperature have an influence on the turbulent drag, the characteristics of the body surface primarily determine the extent of the turbulent drag. For excluding the separation of the boundary layer and producing steady flow of gas or liquid the leading edges of aerodynamic or hydrodynamic components usually are made with smooth surface. DISCLOSURE OF INVENTION
For some types of surfaces of cutting edges the ideal fluid model has no solutions for nfinite velocity. So the appearance of vortexes and the separation of the boundary layer in these cases are impossible or delayed near the cutting edges. As a result the flow is steady there and the turbulent drag is absent. This effect can be used not only for any edge of construction, but for reducing the turbulent drag on the surfaces of bodies as well. For example, for reducing the turbulent drag on the surfaces of aircraft or watercraft units, or on the inner surface of tube. For this purpose we need to create the shape of these surfaces characterized by an array of spaced cutting edges, near which the separation of the boundary layer is delayed or prevented, so the average value of turbulent drag will be reduced.
BRIEF DESCRIPTION OF DRAWINGS
Fig.l, Fig.2, Fig.3 are three different views of surface, for which the claim 1.1 is true in point P.
Fig.4 are surfaces, for which the claim 1.2.1 is true in crossing line between points D and E.
Fig.5 are surfaces, for which the claim 1.2 is true. In crossing line between points F, G and between points G, H the claim 1.2.1 is true. In the point G the claim 1.2.2 is true. Fig.6 and Fig.7 are examples of surface, which has array of spaced cutting edges, for which claim 1.2.1 is true.
Fig.8 is example of surface, which has array of spaced cutting edges, for which the-claim 2 is true: in any point of cutting edge, where flat elements do not touch, the claim Ύ.2Λ is true; in points, where flat elements do touch, the claim 1.2.2 s true. Fig.9 is profile of few crossed surfaces, which can be modified for achieving laminarity of flow of gas or liquid near point P as Fig.10, Fig.l 1 show.
Fig.10 and Fig.l 1 are two variants of modification of profile Fig.9 for achieving laminarity of flow of gas or liquid near point P, where the claim 1.1 is true.
Fig.12 is scheme of bulk carrier with bulbous bow.
Fig.13 is prototype of bulbous bow for bulk carrier, in which the claim 1.1 is true in point A, as Fig.l, Fig.2, Fig.3 show, and the claim 2 is true in the region marked by letter C, where it can be used for surfaces such as in Fig 6, Fig.7 arid Fig.8. Fig.14 is scheme of wind power plant.
Fig.15 is prototype of the blade of wind power plant, where for the leading and trailing edges the claim 1.2.1 is true. These edges are marked by letter B.
Fig.16 and Fig.17 are two views of part of the blade from Fig.15.
Fig.18 is scheme of aircraft showing the regions, where the claims of invention can be used: regions marked by letter A are for the use of claim 1.1; regions marked by letter B are for the use of claim 1.2; regions marked by letter C are for the use of claim 2.
Fig.19 and Fig.20 are two views of the part of prototype for wing of an aircraft with leading-edge slat, where claim 1.2.1 is true for the leading and trailing edges.
MODES FOR CARRYING OUT THE INVENTION
For profile of surface Fig.l, Fig.2, Fig.3 the claim 1.1 is true in point P. It can be used, for example, as part of the bulbous bow Fig.13 in point A of bulk carrier shown in Fig.12. In region, marked by letter C in Fig.13, where the initial boundary layer separation is possible, the profiles Fig.6, Fig.7, Fig.8 of surface can be used. For profiles Fig.6, Fig.7 and Fig.8 of surface the claim 2 is true. The average value of turbulent drag reduces near these surfaces.
For construction of wind power plant shown in Fig.14 the variant of blade shown in Fig.15, Fig.16 and Fig 17 can be used. For the leading and trailing cutting edges of the blade, marked by letter B in Fig.15, that are shown in Fig.16 and Fig.17, the claim 1.2.1 is true. This profile with the cutting edge is an alternative to the profile of smooth surface, in which the drag of laminar flow near leading cutting edge is generally lower. The trailing cutting edge, for which the claim 1.2 is true, is also preferred to the profile of smooth surface or traditional trailing cutting edge with profile of a wedge, because the appearance of vortex near this cutting edge is delayed or prevented.
In the aircraft's construction, Fig.18, there is possibility for the use the invention in the regions, marked by letters A, B, C. In the regions, marked by letter A, the claim 1.1 can be used. The variants for this use are shown in Fig.l, Fig.2, Fig.3 and in Fig.10, Fig.l 1 as well. For the profiles shown in Fig.10, Fig.l 1 , initial profile of surface is shown in Fig.9 . Although the variant with solitary point as cutting edge is preferred, the achieving of laminarity of flow near some point on the line of cutting edge or the crossing of cutting edges, as shown in Fig.9 in point P, is also possible. In this case
Q A MEUairUITT/II ΤΤΠΓΤ the benefit of the invention applies to the point P only, and the separation of the boundary layer on the cutting edges, which are crossed in the point P in Fig.10, Fig.11 , is still possible. For these cutting edges the claims 1.2.1, 1.2.2 can be additionally used, as it is shown in Fig.4 and Fig.5 .
In the regions that are marked by letter B, claim 1.2 can be used in same manner, as it was described for the blade of a wind power plant above. Fig.19 and Fig.20
are showing the prototype of wing with the leading-edge slat for aircraft.
In the regions marked by letter C, claim 2 can be used for reducing the extent of turbulent drag by delaying or preventing the separation of the boundary layer there. Fig.6, Fig.7 and Fig.8 are showing some of possible profiles of such surfaces, for which the claim 2 is true. The profile in Fig.8 is more suitable for places, where the flow can change direction.
The claim 2 and surfaces Fig.6, Fig.7, Fig.8 can be used for reducing the turbulent 4rag of the surfaces of tubes or underwater constructions.
DESCRIPTION OF THE PREFERED EMBODIMENT
The best mode for carrying out the invention includes full realization of claims conditions in part of surface near a cutting edge.
For claim 1.1 the best mode is the embodiment of the surface, which touches the cones with different aperture angles in maximum possible number of tangent rays in the point of cutting edge.
For claim 1.2 the best mode is the embodiment, when one of crossing surface is plane.
For claim 2 the best mode is the embodiment, where an array of spaced cutting edges lays in the regions, where the initial separation of the boundary layer is possible.
The most appropriate scale factor is related to the Reynolds-number and to other not mentioned here parameters, so it can be recognized by testing of a few models.

Claims

CLAIMS I claim:
1. An aerodynamic or hydrodynamic component having a cutting edge with significant profile of surface near it.
1.1 If the cutting edge is point, there are two o more cones with not equal aperture angles, everyone of which has three or more various tangent rays
to the surface in this point.
1.2 If the cutting edge is line, the profile consists of two smooth surfaces, which have crossing in this line. In each point of this line one of two conditions is true:
1.2.1 There is a conical surface, which has three or more various tangent lines to one of these two surfaces in this point, or there is a tangent plane to it in this point. Conical surface, which has three or more various tangent lines to another of these two surfaces in this point or tangent plane to it in this point, does not exist.
1.2.2 There are segments of conical surfaces or planes, which have three or more various tangent lines to one of these two surfaces in this point. It is impossible to find pair of the segments with weighted means of normal to the segments located in one plane.
2. An aerodynamic or hydrodynamic component having a surface with an array of spaced cutting edges, for which claim 1.2 is true at least on some length.
The distinguishing features are the significant profiles of surface near cutting edge.
The term "cutting edge" means the possible technical accuracy of performance and ultimate condition as point or line.
The term "cone" means right circular cone.
The term "conical surface" means the surface formed by the union of all
the straight lines, that pass through a fixed point and any point of some fixed space curve, that does not contain the apex.
3AMEH9K)IIMH JIMCT
PCT/RU2013/001035 2013-11-19 2013-11-19 Method and apparatus for achieving laminar flow of gas or liquid near cutting edges WO2014109670A2 (en)

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112977713A (en) * 2021-04-07 2021-06-18 浙江海洋大学 Vortex generator for propeller type ship and ship

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1992005341A1 (en) * 1990-09-14 1992-04-02 Josef Moser Rotor
DE4208751A1 (en) * 1992-02-27 1993-11-11 Fritz Karl Hausser Reducing resistance to aerofoil or hydrofoil passing through medium e.g. air or water - uses array of teeth formed on leading and/or trailing edge of aerofoil or hydrofoil section
RU2294300C2 (en) * 2005-03-22 2007-02-27 Институт теоретической и прикладной механики СО РАН (ИТПМ СО РАН) Lifting surface

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1992005341A1 (en) * 1990-09-14 1992-04-02 Josef Moser Rotor
DE4208751A1 (en) * 1992-02-27 1993-11-11 Fritz Karl Hausser Reducing resistance to aerofoil or hydrofoil passing through medium e.g. air or water - uses array of teeth formed on leading and/or trailing edge of aerofoil or hydrofoil section
RU2294300C2 (en) * 2005-03-22 2007-02-27 Институт теоретической и прикладной механики СО РАН (ИТПМ СО РАН) Lifting surface

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112977713A (en) * 2021-04-07 2021-06-18 浙江海洋大学 Vortex generator for propeller type ship and ship

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