DE893892C - Aircraft wing, propeller wing or the like with a cavity extending inside to the wing end and provided with inlet openings - Google Patents
Aircraft wing, propeller wing or the like with a cavity extending inside to the wing end and provided with inlet openingsInfo
- Publication number
- DE893892C DE893892C DEL12665A DEL0012665A DE893892C DE 893892 C DE893892 C DE 893892C DE L12665 A DEL12665 A DE L12665A DE L0012665 A DEL0012665 A DE L0012665A DE 893892 C DE893892 C DE 893892C
- Authority
- DE
- Germany
- Prior art keywords
- wing
- inlet openings
- propeller
- aircraft
- cavity
- 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
- B64C23/00—Influencing air flow over aircraft surfaces, not otherwise provided for
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
Description
Es ist bekannt, daß beim fliegenden Luftfahrzeug am äußeren Ende des Tragflügels ein Wirbelgebiet vorhanden ist, das der Geschwindigkeit des Luftfahrzeuges einen erheblichen Widerstand entgegensetzt. Von der unterenTragflügelseite(Druckseite) wirbelt Luft um das äußere Ende des Tragflügels auf seine Oberseite (Sogseite) und bildet dabei den sogenannten Wirbelzopf oder induzierten Widerstand.It is known that when flying aircraft at the outer end of the Wing there is a vortex area that corresponds to the speed of the aircraft opposed considerable resistance. From the lower wing side (pressure side) swirls air around the outer end of the wing onto its top (suction side) and forms the so-called vortex braid or induced drag.
Die Erfindung bezweckt die Herabsetzung des induzierten Widerstandes dadurch, daß Luft durch Einlaßöffnungen, die an der unteren, vorderen Seite des Flügels :angebracht sind, in einen im Innern des Flügels befindlichen, bis an das Flügelende sich erstreckenden Hohlraum eintritt und in diesem so geführt wird, daß eine kreisende Bewegung im Sinne einer vorwärts rollenden Walze entsteht und am Flügelende zwecks Unterdrückung des Randwirbels austritt.The invention aims to reduce the induced drag by letting air through inlet openings on the lower, front side of the Wing: are attached, in one located inside the wing, up to the Wing tip extending cavity enters and is guided in this so that a circular movement in the sense of a forward rolling roller is created and on Wing tip emerges for the purpose of suppressing the tip vortex.
Vorteilhaft liegen die Einlaßöffnungen auf der Druckseite des Flügels und `haben eine solche Form, daß sie luftfangend wirken.The inlet openings are advantageously on the pressure side of the wing and `have such a shape that they have an air-catching effect.
Der Hohlraum bildet zweckmäßig eine Röhre von möglichst großem Durchmesser und liegt im Vorderteil des Flügels.The cavity expediently forms a tube with the largest possible diameter and lies in the front part of the wing.
Die Erfindung ist in .der Zeichnung beispielsweise und schematisch dargestellt und zeigt die Einrichtung mit dem Verlauf der Strömung an einem Tragflügelstück.The invention is in .der drawing example and schematically shown and shows the device with the course of the flow on a wing piece.
Am Tragflügel r ist ein Schlitz 2 an der unteren vorderen Seite so ausgebildet, daß er in Fluglage die benötigte Luft fängt. Im Rohr 3 wird die eintretende Luft in Drehrichtung der Pfeile 4 in Drehung gebracht und zum Flügelende abgeleitet. Dort tritt sie am offenen Rohrende aus und trifft mit dem Wirbelzopf zusammen, der durch punh tierte Pfeile 5 gekennzeichnet ist. Da beide Wirbelstraßen entgegengesetzte Drohrichtung haben, heben sie sich auf. Die rotierende Luftwalze in den Flügeln übt durch ihre Kreiselwirkung eine stabilisierende Wirkung auf das Flugzeug aus.On the wing r there is a slot 2 on the lower front side trained that it catches the required air in flight. In the pipe 3 is the incoming Air brought into rotation in the direction of rotation of arrows 4 and diverted to the wing tip. There it emerges at the open end of the pipe and meets the pigtail of the vortex, the is indicated by dotted arrows 5. Since both vortex streets are opposite Have a threatening direction, they cancel each other out. The rotating air cylinder in the wings has a stabilizing effect on the aircraft due to its gyroscopic effect.
Claims (5)
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DEL12665A DE893892C (en) | 1952-06-22 | 1952-06-22 | Aircraft wing, propeller wing or the like with a cavity extending inside to the wing end and provided with inlet openings |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DEL12665A DE893892C (en) | 1952-06-22 | 1952-06-22 | Aircraft wing, propeller wing or the like with a cavity extending inside to the wing end and provided with inlet openings |
Publications (1)
Publication Number | Publication Date |
---|---|
DE893892C true DE893892C (en) | 1953-10-19 |
Family
ID=7259258
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
DEL12665A Expired DE893892C (en) | 1952-06-22 | 1952-06-22 | Aircraft wing, propeller wing or the like with a cavity extending inside to the wing end and provided with inlet openings |
Country Status (1)
Country | Link |
---|---|
DE (1) | DE893892C (en) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE3836673A1 (en) * | 1988-10-28 | 1990-05-03 | Michael Harriehausen | Method and arrangement for reducing the induced drag of a wing |
US5054720A (en) * | 1989-09-18 | 1991-10-08 | Mcdonnell Douglas Corporation | Trapped vortex cavity |
Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR729821A (en) * | 1931-01-16 | 1932-08-01 | Improvements made to devices comprising surfaces which must coact with a fluid. especially to airplanes | |
US2075817A (en) * | 1934-08-17 | 1937-04-06 | Arthur W Loerke | Wing vortex reducer |
FR971992A (en) * | 1940-12-07 | 1951-01-24 | Jet-propelled aerial vehicles improvements |
-
1952
- 1952-06-22 DE DEL12665A patent/DE893892C/en not_active Expired
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR729821A (en) * | 1931-01-16 | 1932-08-01 | Improvements made to devices comprising surfaces which must coact with a fluid. especially to airplanes | |
US2075817A (en) * | 1934-08-17 | 1937-04-06 | Arthur W Loerke | Wing vortex reducer |
FR971992A (en) * | 1940-12-07 | 1951-01-24 | Jet-propelled aerial vehicles improvements |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE3836673A1 (en) * | 1988-10-28 | 1990-05-03 | Michael Harriehausen | Method and arrangement for reducing the induced drag of a wing |
US5054720A (en) * | 1989-09-18 | 1991-10-08 | Mcdonnell Douglas Corporation | Trapped vortex cavity |
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