DE420325C - Device for damping tip vortices on aircraft wings u. like - Google Patents
Device for damping tip vortices on aircraft wings u. likeInfo
- Publication number
- DE420325C DE420325C DEM83866D DEM0083866D DE420325C DE 420325 C DE420325 C DE 420325C DE M83866 D DEM83866 D DE M83866D DE M0083866 D DEM0083866 D DE M0083866D DE 420325 C DE420325 C DE 420325C
- Authority
- DE
- Germany
- Prior art keywords
- tip vortices
- aircraft wings
- damping
- damping tip
- wing
- 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
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/16—Blades
Description
Vorrichtung --zur Dämpfung von Randwirbeln an Flugzeug -Tragflächen u. dgl. Die in der Zeichnung beispielsweise an einer Flugzeug-Tragfläche (Abb. i) und einem Schraubenpropeller (Abb. a) dargestellte ErfIndung bezweckt die Dämpfung der Randwirbel, welche sich an der Tragfläche infolge des dynamischen Antriebes bilden und hier wie beim Propeller den Wirkungsgrad ungünstig beeinflussen. Sie bezweckt außerdem eine mit der Wirbeldämpfung zugleich erfolgende Verjüngung des Flügelkörpers durch dieselben Schlitze nach der Hinterkante des Flügels, um eine unter geringstem Widerstand erfolgende allmähliche Loslösung des Flügelklörpers vom' luftförmigen Körper zu erzielen. De Erfindung besteht darin, daß in der Tragfläche (Abb. i) dort, wo sich Hohlräume und Wirbel bilden, sich in der Bewegungsrichtung Schlitze a, b erstrecken, welche Schlitze nach der Wirbelkante. hin breiter werden, damit die Luft in einer der Randwirbelbildung entsprechenden, nach hinten allmählich zunehmenden Menge von der Druck- nach der Saugseite gelangen kann. Durch jeden. Schlitz strömt also eine der jeweiligen. Wirbelentwickelung entsprechende, allmählich von einem Minimum bis zu einem Maximum nach der Wirbelkante :sich steigernde Luftmenge zur allmählichen Dämpfung der Wirbel, während gleichzeitig der Flügelkörper durch dieselben Schlitze nach der Wirbelkante allmählich verjüngt wird und sich unter geringstem Widerstand vom luftförmigen Körper loslösen kann. Eine solche Vorrichtung wird stets dort mit Erfolg verwendet werden können, wo ein starres Antriebsmittel in einem luftförmigen oder flüssigen Körper bewegt wird.Device - for damping tip vortices on aircraft wings and the like. The invention shown in the drawing, for example on an aircraft wing (Fig. I) and a screw propeller (Fig Form the wing as a result of the dynamic drive and here, as with the propeller, have an unfavorable effect on the efficiency. It also aims to taper the wing body through the same slots towards the trailing edge of the wing at the same time as the vortex damping, in order to achieve a gradual detachment of the wing body from the air-shaped body with the least possible resistance. The invention consists in the fact that in the wing (Fig. I) where cavities and vortices are formed, slots a, b extend in the direction of movement, which slots extend towards the edge of the vortex. become wider so that the air can get from the pressure side to the suction side in an amount corresponding to the formation of the tip vortices and gradually increasing towards the rear. By everyone. One of the respective slots flows through the slot. Vortex development, gradually from a minimum to a maximum after the edge of the vortex: increasing amount of air to gradually dampen the vortex, while at the same time the wing body is gradually tapered through the same slits after the vortex edge and can detach itself from the air-shaped body with the least resistance. Such a device will always be able to be used with success where a rigid drive means is moved in an air-shaped or liquid body.
Claims (1)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DEM83866D DE420325C (en) | Device for damping tip vortices on aircraft wings u. like |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DEM83866D DE420325C (en) | Device for damping tip vortices on aircraft wings u. like |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| DE420325C true DE420325C (en) | 1925-10-19 |
Family
ID=7319737
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| DEM83866D Expired DE420325C (en) | Device for damping tip vortices on aircraft wings u. like |
Country Status (1)
| Country | Link |
|---|---|
| DE (1) | DE420325C (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5088665A (en) * | 1989-10-31 | 1992-02-18 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Serrated trailing edges for improving lift and drag characteristics of lifting surfaces |
| 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 |
| DE102005054248A1 (en) * | 2005-11-15 | 2007-05-24 | Airbus Deutschland Gmbh | Braking flap for deceleration of aircraft against air-flow which surrounds aircraft, comprises many vortex edges, which resolve individual edge section into number of vortex part, are arranged at free edge |
| WO2007065434A1 (en) * | 2005-12-05 | 2007-06-14 | Lm Glasfiber A/S | Blade for a wind turbine rotor |
| DE102006049616A1 (en) * | 2006-10-20 | 2008-04-30 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Aerodynamic component has slits at the trailing edge, running between the upper and lower main surfaces, to reduce air turbulence noise emissions |
-
0
- DE DEM83866D patent/DE420325C/en not_active Expired
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5088665A (en) * | 1989-10-31 | 1992-02-18 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Serrated trailing edges for improving lift and drag characteristics of lifting surfaces |
| 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 |
| DE102005054248A1 (en) * | 2005-11-15 | 2007-05-24 | Airbus Deutschland Gmbh | Braking flap for deceleration of aircraft against air-flow which surrounds aircraft, comprises many vortex edges, which resolve individual edge section into number of vortex part, are arranged at free edge |
| WO2007065434A1 (en) * | 2005-12-05 | 2007-06-14 | Lm Glasfiber A/S | Blade for a wind turbine rotor |
| CN101321949B (en) * | 2005-12-05 | 2013-03-13 | Lm玻璃纤维制品有限公司 | Blade for a wind turbine rotor |
| DE102006049616A1 (en) * | 2006-10-20 | 2008-04-30 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Aerodynamic component has slits at the trailing edge, running between the upper and lower main surfaces, to reduce air turbulence noise emissions |
| DE102006049616B4 (en) * | 2006-10-20 | 2010-08-05 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Arrangement of an aerodynamic component with a slotted rear or side edge in a flow |
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