DE845900C - Device for influencing the boundary layer on all types of bodies - Google Patents

Device for influencing the boundary layer on all types of bodies

Info

Publication number
DE845900C
DE845900C DEK6623D DEK0006623D DE845900C DE 845900 C DE845900 C DE 845900C DE K6623 D DEK6623 D DE K6623D DE K0006623 D DEK0006623 D DE K0006623D DE 845900 C DE845900 C DE 845900C
Authority
DE
Germany
Prior art keywords
boundary layer
influencing
bodies
types
flow
Prior art date
Legal status (The legal status 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 status listed.)
Expired
Application number
DEK6623D
Other languages
German (de)
Inventor
Freiherr Re Koenig-Fachsenfeld
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Individual
Original Assignee
Individual
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
Application filed by Individual filed Critical Individual
Priority to DEK6623D priority Critical patent/DE845900C/en
Application granted granted Critical
Publication of DE845900C publication Critical patent/DE845900C/en
Expired legal-status Critical Current

Links

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
    • 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

Description

Die Erfindung bezieht sich auf eine Einrichtung zur Beeinflussung der'Grenzschitht-an Körpern allerArt: Es ist bekannt, zur Beschleunigung der infolge Druckanstiegs an der Körperoberfläche allmählich erlahmenden und zum Rückströmen neigenden Grenz-Schicht Stufen quer zur Strömungsrichtung anzuordnen. Ferner sind Tragflügel und Leitflächen mit wellenartig profilierter Oberfläche bekannt.The invention relates to a device for influencing der'Grenzschitht-an bodies of all kinds: it is known to accelerate the result Pressure increase on the body surface gradually waning and flowing back inclined boundary layer to arrange steps transversely to the direction of flow. Furthermore are Airfoils and guide surfaces with a wave-like profiled surface are known.

Die Erfindung geht demgegenüber von der Erkennt-, nis -aus, daß der bei Druckanstieg allmählich erlahmenden und zur Rückströmung neigenden Grenzschicht neue Energie am besten durch eine innige Vermischung mit der Hauptströmung zugeführt wird.: Dies wird erfindungsgemäß dadurch erreicht, daß an den Stellen der Körperoberfläche, an denen die Grenzschicht erlahmt und an Dicke zunimmt, in Strömungsrichtung verlaufende, rippenartige Profile angeordnet sind, deren Höhe ungefähr gleich der Grenzschichtdicke ist. Durch die hierdurch verur-, sachte Strömungsquerschnittsverengung wird die Grenzschicht gezwungen, nach oben auszuweichen, wo sie sich mit der Hauptströmung vermischt, die ihr neue Energie zuführt. Insgesamt . wird dadurch ein längeres Anliegen der Strömung erreicht.The invention is based on the knowledge, nis -from that the when the pressure rises, the boundary layer gradually weakens and tends to reverse flow new energy is best supplied through intimate mixing with the main flow is .: This is achieved according to the invention in that at the points on the body surface, at which the boundary layer weakens and increases in thickness, running in the direction of flow, Rib-like profiles are arranged, the height of which is approximately equal to the boundary layer thickness is. Due to the gentle flow cross-section narrowing caused by this, the Boundary layer forced to move upwards, where it meets the main flow mixed, which supplies her with new energy. All in all . it becomes a longer concern reached the flow.

Die Profile können je nach den strömungstechnischen Erfordernissen verschiedenartige Höhe, Form, Länge und gegenseitigen Abstand haben. Sie können z: B: auch Keilform haben. Die Höhe der Profile, die ungefähr der Grenzschichtdicke entspricht, sowie deren Form und Abstand können sich über ihre Länge ändern. Auch kann die Körperoberfläche selbst entsprechend verformt sein.The profiles can depending on the fluidic requirements have different height, shape, length and mutual distance. You can z: B: also have a wedge shape. The height of the profiles, which is approximately the boundary layer thickness corresponds, as well as their shape and distance can change over their length. Even the body surface itself can be deformed accordingly.

In der Zeichnung ist ein Ausführungsbeispiel der Erfindung schaubildlich dargestellt. Auf der Oberseite xtnd am Hinterende eines Tragflügelkörpers, an dem die Strömung zum Ablösen neigt, sind rippenartige, näcii hinten höher und breiter werdende Profile angebracht, die bis an die Hinterkante des Körpers reichen. Die Profile sind hinten geschlossen. Sie können jedoch :mit Vorteil auch nach hinten offen bleiben' und durch sie z. B. bei Kraftfahrzeugen Kühlluft oder Abgase ausgeblasen werden.An exemplary embodiment of the invention is shown diagrammatically in the drawing shown. On the top xtnd at the rear end of a wing body on which the flow tends to detach, are rib-like, necii higher and wider at the back attached profiles that reach to the rear edge of the body. the Profiles are closed at the back. However, you can: with advantage also to the rear stay open 'and through them z. B. blown out cooling air or exhaust gases in motor vehicles will.

Claims (1)

PATI:hTANSl'HU(:I1: Einrichtung zur Beeinflussung der Grenzschicht an Körpern aller Art, dadurch gekennzeichnet, däß deren Oberfläche im Bereich verzögerter Grenzschichtströmung in Strömungsrichtung verlaufende, rippenartige Profile trägt, deren Höhe ungefähr der Grenzschichtdicke entspricht.PATI: hTANSl'HU (: I1: Device for influencing the boundary layer on bodies of all types, characterized in that their surface is delayed in the area Boundary layer flow carries rib-like profiles running in the direction of flow, the height of which corresponds approximately to the thickness of the boundary layer.
DEK6623D 1943-08-07 1943-08-07 Device for influencing the boundary layer on all types of bodies Expired DE845900C (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
DEK6623D DE845900C (en) 1943-08-07 1943-08-07 Device for influencing the boundary layer on all types of bodies

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DEK6623D DE845900C (en) 1943-08-07 1943-08-07 Device for influencing the boundary layer on all types of bodies

Publications (1)

Publication Number Publication Date
DE845900C true DE845900C (en) 1952-08-07

Family

ID=7211357

Family Applications (1)

Application Number Title Priority Date Filing Date
DEK6623D Expired DE845900C (en) 1943-08-07 1943-08-07 Device for influencing the boundary layer on all types of bodies

Country Status (1)

Country Link
DE (1) DE845900C (en)

Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2967030A (en) * 1957-11-13 1961-01-03 Richard T Whitcomb Boundary-layer control means for lifting wings
DE3202812A1 (en) * 1982-01-26 1983-08-04 Werner 1000 Berlin Schlick Wind deflector
US4699340A (en) * 1983-11-07 1987-10-13 Vehicle Research Corporation Laminar vortex pump system
US4736912A (en) * 1985-06-27 1988-04-12 Messerschmitt-Boelkow-Blohm Gmbh Apparatus for reducing turbulent drag
EP0273850A2 (en) * 1986-12-29 1988-07-06 United Technologies Corporation Bodies with reduced base drag
US4776535A (en) * 1986-12-29 1988-10-11 United Technologies Corporation Convoluted plate to reduce base drag
US4813635A (en) * 1986-12-29 1989-03-21 United Technologies Corporation Projectile with reduced base drag
US4813633A (en) * 1986-12-29 1989-03-21 United Technologies Corporation Airfoil trailing edge
US4830315A (en) * 1986-04-30 1989-05-16 United Technologies Corporation Airfoil-shaped body
WO1993019981A1 (en) * 1992-03-31 1993-10-14 Rolls-Royce Plc Control of fluid flow
WO1993019980A1 (en) * 1992-03-31 1993-10-14 Rolls-Royce Plc Control of fluid flow
US5575442A (en) * 1995-01-19 1996-11-19 The United States Of America As Represented By The Secretary Of The Navy Guided wing for aircraft flying at high angles of attack
DE19634296A1 (en) * 1996-08-24 1997-04-24 Erich Dipl Ing Ufer Aircraft fan jet propulsion unit
FR2948906A1 (en) * 2009-08-07 2011-02-11 Peugeot Citroen Automobiles Sa Trim i.e. multifunctional rear trim, for use in dome of motor vehicle, has navigation and/or radio reception antenna, stoplamp, backup camera and protrusions, where trim is made of organic glass molded by layer of plastic material
CN102187063A (en) * 2008-10-13 2011-09-14 斯奈克玛 Turbine blade with improved aerodynamic performance

Cited By (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2967030A (en) * 1957-11-13 1961-01-03 Richard T Whitcomb Boundary-layer control means for lifting wings
DE3202812A1 (en) * 1982-01-26 1983-08-04 Werner 1000 Berlin Schlick Wind deflector
US4699340A (en) * 1983-11-07 1987-10-13 Vehicle Research Corporation Laminar vortex pump system
US4736912A (en) * 1985-06-27 1988-04-12 Messerschmitt-Boelkow-Blohm Gmbh Apparatus for reducing turbulent drag
US4830315A (en) * 1986-04-30 1989-05-16 United Technologies Corporation Airfoil-shaped body
US4776535A (en) * 1986-12-29 1988-10-11 United Technologies Corporation Convoluted plate to reduce base drag
US4789117A (en) * 1986-12-29 1988-12-06 United Technologies Corporation Bodies with reduced base drag
EP0273850A3 (en) * 1986-12-29 1989-02-22 United Technologies Corporation Bodies with reduced base drag
US4813635A (en) * 1986-12-29 1989-03-21 United Technologies Corporation Projectile with reduced base drag
US4813633A (en) * 1986-12-29 1989-03-21 United Technologies Corporation Airfoil trailing edge
EP0273850A2 (en) * 1986-12-29 1988-07-06 United Technologies Corporation Bodies with reduced base drag
WO1993019980A1 (en) * 1992-03-31 1993-10-14 Rolls-Royce Plc Control of fluid flow
WO1993019981A1 (en) * 1992-03-31 1993-10-14 Rolls-Royce Plc Control of fluid flow
US5542630A (en) * 1992-03-31 1996-08-06 Rolls-Royce Plc Control of fluid flow
US5575442A (en) * 1995-01-19 1996-11-19 The United States Of America As Represented By The Secretary Of The Navy Guided wing for aircraft flying at high angles of attack
DE19634296A1 (en) * 1996-08-24 1997-04-24 Erich Dipl Ing Ufer Aircraft fan jet propulsion unit
DE19634296C2 (en) * 1996-08-24 1999-04-22 Erich Dipl Ing Ufer Blower engine for aircraft with facilities for boundary layer extraction
CN102187063A (en) * 2008-10-13 2011-09-14 斯奈克玛 Turbine blade with improved aerodynamic performance
US8794926B2 (en) 2008-10-13 2014-08-05 Snecma Turbine blade with improved aerodynamic performance
CN102187063B (en) * 2008-10-13 2015-01-14 斯奈克玛 Turbine blade with improved aerodynamic performance
FR2948906A1 (en) * 2009-08-07 2011-02-11 Peugeot Citroen Automobiles Sa Trim i.e. multifunctional rear trim, for use in dome of motor vehicle, has navigation and/or radio reception antenna, stoplamp, backup camera and protrusions, where trim is made of organic glass molded by layer of plastic material

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