JPH0454079Y2 - - Google Patents
Info
- Publication number
- JPH0454079Y2 JPH0454079Y2 JP1987075208U JP7520887U JPH0454079Y2 JP H0454079 Y2 JPH0454079 Y2 JP H0454079Y2 JP 1987075208 U JP1987075208 U JP 1987075208U JP 7520887 U JP7520887 U JP 7520887U JP H0454079 Y2 JPH0454079 Y2 JP H0454079Y2
- Authority
- JP
- Japan
- Prior art keywords
- wing
- small
- main wing
- main
- vortex
- 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
Landscapes
- Structures Of Non-Positive Displacement Pumps (AREA)
- Toys (AREA)
Description
【考案の詳細な説明】
〔産業上の利用分野〕
本考案は、航空機の誘導抵抗を減少し、また他
機への翼端渦の影響を減少するための航空機翼端
渦減少装置に関する。[Detailed Description of the Invention] [Industrial Application Field] The present invention relates to an aircraft wing tip vortex reduction device for reducing the induced drag of an aircraft and also reducing the influence of the wing tip vortex on other aircraft.
従来は、主翼の翼端に存在する渦による誘導抵
抗を減少させるために、主翼の翼端部に端板、タ
ービンまたはプロペラを装着していた。
Conventionally, end plates, turbines, or propellers have been attached to the tips of the main wings in order to reduce the induced resistance due to vortices existing at the tips of the main wings.
通常の航空機の主翼の翼端には第６図に示すよ
うな翼端渦４が存在し、主翼の誘導抵抗を増加し
て性能悪化をきたしたり、大きな航空機から発生
する翼端渦の中に小型機が入ると小型機に悪影響
を及ぼして事故につながつたりする問題があつ
た。
A wing tip vortex 4 as shown in Figure 6 exists at the tip of the main wing of a normal aircraft, which increases the induced resistance of the main wing and causes performance deterioration. There was a problem that if small aircraft entered the system, it would have a negative impact on the small aircraft, leading to accidents.
このため、従来は、主翼１の端に端板をつけた
り、タービンまたはプロペラをとりつけて翼端渦
を弱めていた。これらの方法では大きな端板をと
りつけたり、複雑なタービンまたはプロペラをと
りつけたりして大工事となり、主翼付根部の補強
を要したり、重量増加をきたしたりしていた。 For this reason, conventionally, end plates were attached to the ends of the main wings 1, or turbines or propellers were attached to weaken the wing tip vortices. These methods required major construction work, such as the installation of large end plates, complex turbines or propellers, required reinforcement of the wing roots, and increased weight.
この考案は、以上の問題点を解消して、航空機
の性能を維持し他機への影響を少くすることを目
的とする。 The purpose of this invention is to solve the above problems, maintain the performance of the aircraft, and reduce the impact on other aircraft.
この目的を達成させるためにこの考案では、主
翼端部の上面と下面の少くとも一方の端部に主翼
に対して小間隔をおいてほぼ平行に装着された小
翼を設け、この小翼の主翼翼根側の前縁の後退角
が主翼翼端側の前縁の後退角より小さく設定され
ている。
In order to achieve this purpose, in this invention, a small wing is installed on at least one end of the upper and lower surfaces of the main wing tip, and is mounted approximately parallel to the main wing at a small distance. The sweepback angle of the leading edge on the root side of the main wing is set smaller than the sweepback angle of the leading edge on the tip side of the main wing.
この考案では、主翼の翼端部の上面と下面の少
くとも一方の前部に主翼に対して小間隔をおいて
ほぼ平行に装着された小翼を設け、この小翼の主
翼翼根側の前縁の後退角を主翼翼端側の前縁の後
退角より小さくしている。以上のように構成され
た小翼においては、その前縁の翼端ではく離した
流れは小翼の上面に一対の渦を生ずる。この場
合、小翼の主翼翼根側の前縁で生ずる渦の方向と
主翼の翼端渦の方向とは反対であり、小翼の主翼
翼端側の前縁で生ずる渦の方向と主翼翼端渦の方
向は同じであり、かつ、小翼の主翼翼根側の前縁
の後退角が主翼翼端側の前縁の後退角より小さい
ために、前者で発生する渦は後者で発生する渦よ
り大きい。従つて、全体として小翼によつて主翼
の翼端で発生する渦と反対方向の渦が発生するこ
ととなり、主翼の翼渦を弱めることになる。
In this design, a small wing is installed approximately parallel to the main wing at a small distance in front of at least one of the upper and lower surfaces of the wing tip of the main wing, and the main wing root side of this small wing is The sweeping angle of the leading edge is made smaller than the sweeping angle of the leading edge on the wing tip side of the main wing. In the winglet configured as described above, the flow separated at the tip of the leading edge generates a pair of vortices on the upper surface of the winglet. In this case, the direction of the vortex generated at the leading edge on the root side of the main wing of the small wing is opposite to the direction of the tip vortex of the main wing, and the direction of the vortex generated at the leading edge of the small wing on the side of the main wing tip is opposite to the direction of the vortex on the main wing root side. The directions of the end vortices are the same, and the sweepback angle of the leading edge on the root side of the main wing of the small wing is smaller than the sweepback angle of the leading edge on the tip side of the main wing, so the vortices generated in the former are generated in the latter. Bigger than a vortex. Therefore, as a whole, the small blades generate vortices in the opposite direction to the vortices generated at the tips of the main wings, weakening the vortices of the main wings.
この考案の一実施例を第１図ないし第５図を参
照して説明する。通常の航空機では第５図に示す
ように主翼により翼端渦４が発生し、これによ
り、主翼の誘導抵抗を増加し、また大型機の翼端
渦の中へ小型機が飛行してくると小型機がひつく
りかえつて事故になることもある。
An embodiment of this invention will be described with reference to FIGS. 1 to 5. In a normal aircraft, a wingtip vortex 4 is generated by the main wing as shown in Figure 5, which increases the induced resistance of the main wing, and when a small aircraft flies into the wingtip vortex of a large aircraft. Accidents can also occur when small planes switch back and forth.
本実施例では、第１図に示すように主翼１の両
翼端部の上面前部に主翼上面より小間隔をおい
て、主翼１にほぼ平行に三角形の小翼３を支柱２
を介して装着する。同小翼３は、第２図及び第３
図に示すように、三角翼状の形状を有しており、
その主翼翼根側の前縁３−１の後退角α−１は、
その主翼翼端側の前縁３−２の後退角α−２より
小さいように設定されている。 In this embodiment, as shown in FIG. 1, a triangular small wing 3 is installed on the front part of the upper surface of both wing ends of the main wing 1, at a distance from the upper surface of the main wing, and approximately parallel to the main wing 1.
Attach via. The small wing 3 is shown in Figures 2 and 3.
As shown in the figure, it has a triangular wing shape,
The sweeping angle α-1 of the leading edge 3-1 on the root side of the main wing is:
It is set to be smaller than the sweepback angle α-2 of the leading edge 3-2 on the wing tip side of the main wing.
本実施例においては、航空機の飛行に当つて、
小翼３は主翼１と同様に流れに対して迎角をもつ
ているが、三角翼状の小翼３の前縁３−１，３−
２において流れがはく離して、第４図に示すよう
に小翼３の上面に一対の渦Ａ，Ｂを発生する。前
記渦Ａの方向は、第６図に示す主翼による翼端渦
４の方向と逆であり、前記渦Ｂの方向は主翼によ
る翼端渦４の方向と同じである。また前記前縁３
−１の後退角α−１は前記後縁３−２の後退角α
−２より小さいために、第４図に示すように、前
縁３−１で発生する渦Ａは前縁３−２で発生する
渦Ｂより大きい。従つて、第５図に示すように、
全体として小翼３によつて渦５を発生することに
なる。第５図に示すように、この小翼３によつて
発生する渦５は、主翼による翼端渦４と反対方向
である。 In this example, during flight of the aircraft,
The small wing 3 has an angle of attack with respect to the flow similar to the main wing 1, but the leading edges 3-1, 3- of the small wing 3 in the shape of a triangular wing
2, the flow separates and generates a pair of vortices A and B on the upper surface of the small wing 3, as shown in FIG. The direction of the vortex A is opposite to the direction of the wing tip vortex 4 caused by the main wing shown in FIG. 6, and the direction of the vortex B is the same as the direction of the wing tip vortex 4 caused by the main wing. Further, the leading edge 3
-1 is the swept angle α-1 of the trailing edge 3-2.
-2, the vortex A generated at the leading edge 3-1 is larger than the vortex B generated at the leading edge 3-2, as shown in FIG. Therefore, as shown in Figure 5,
As a whole, a vortex 5 is generated by the small blade 3. As shown in FIG. 5, the vortex 5 generated by the small wing 3 is in the opposite direction to the tip vortex 4 caused by the main wing.
従つて、本実施例にあつては、主翼による翼端
渦４と反対方向の渦５が小翼３によつて発生して
主翼による翼端渦４を打ち消し、これを弱めるこ
とができる。この結果、主翼の誘導抵抗が減少
し、他機への翼端渦の影響も少くなつて、性能を
維持してかつ安全に飛行できる。 Therefore, in this embodiment, a vortex 5 in the opposite direction to the tip vortex 4 caused by the main wing is generated by the small wing 3, thereby canceling out the tip vortex 4 caused by the main wing, thereby weakening it. As a result, the induced drag on the main wing is reduced, and the influence of the wingtip vortices on other aircraft is also reduced, allowing for safe flight while maintaining performance.
航空機の迎角が増大して主翼の後流中に小翼３
が入ると渦の発生が困難となるので、上記小翼３
は主翼の前部に配設されるが、第１図に示すよう
に小翼３の一部分が主翼１の前縁より前方に位置
させるのがより強力な渦を発生させるために有利
である。 The angle of attack of the aircraft increases and the small wing 3 is in the wake of the main wing.
If the above small wing 3 enters, it becomes difficult to generate a vortex.
is disposed at the front of the main wing, but as shown in FIG. 1, it is advantageous to position a portion of the small wing 3 forward of the leading edge of the main wing 1 in order to generate a stronger vortex.
また、小翼３の横方向（主翼１の翼巾方向）の
位置は、主翼の翼端渦を打ち消すために主翼翼端
部に位置させる必要があり、主翼半翼巾の約10％
より外側に配置するのが好ましい。 In addition, the position of the small wing 3 in the lateral direction (swidth direction of the main wing 1) needs to be located at the tip of the main wing in order to cancel the wing tip vortices of the main wing, and is approximately 10% of the half width of the main wing.
It is preferable to arrange it further outside.
なお、上記実施例は、主翼の上面に小翼を設け
ているが、下面、又は上面と下面にこれを設けて
主翼の翼端渦を打ち消すようにしてもよい。 In the above embodiment, the small blades are provided on the upper surface of the main wing, but they may be provided on the lower surface, or on the upper and lower surfaces to cancel out the tip vortices of the main wing.
以上のように、この考案によれば、主翼の翼端
部の上面と下面の少くとも一方の前部に主翼に対
して小間隔をおいてほぼ平行に装着された小翼を
設け、かつこの小翼の主翼翼根側の前縁の後退角
を主翼翼端側の前縁の後退角を小さくし、これに
よつて、小翼に前縁で発生する渦によつて主翼の
翼端渦を打ち消すようにすることができる。
As described above, according to this invention, a small wing is provided at the front part of at least one of the upper and lower surfaces of the wing tip of the main wing, and is mounted substantially parallel to the main wing at a small distance. By reducing the sweeping angle of the leading edge on the main wing root side of the small wing and the sweeping angle of the leading edge on the main wing tip side, the vortices generated at the leading edge of the small wing reduce the wing tip vortex of the main wing. can be made to cancel out.
従つて、本考案では、従来問題になつていた主
翼誘導抵抗及び、他機への翼端渦の影響を簡単な
装置で解消し、航空機の性能を維持してかつ安全
に飛行することができる。 Therefore, with this invention, the conventional problems of main wing induced drag and the influence of wing tip vortices on other aircraft can be resolved with a simple device, and the aircraft can maintain its performance and fly safely. .
第１図はその考案の一実施例の正面図、第２図
は同実施例の平面図、第３図は同実施例における
小翼の説明図、第４図は第３図に示す小翼によつ
て発生する渦の説明図、第５図はこの考案の原理
を示す説明図、第６図は主翼による翼端渦を示す
説明図である。
１……主翼、２……支柱、３……小翼、４……
主翼による翼端渦、５……小翼による渦。
Fig. 1 is a front view of an embodiment of the invention, Fig. 2 is a plan view of the embodiment, Fig. 3 is an explanatory diagram of a small wing in the same embodiment, and Fig. 4 is a small wing shown in Fig. 3. FIG. 5 is an explanatory diagram showing the principle of this invention, and FIG. 6 is an explanatory diagram showing the wing tip vortex caused by the main wing. 1...Main wing, 2...Strut, 3...Small wing, 4...
Wing tip vortex caused by the main wing, 5... Vortex caused by the small wing.
Claims (1)
部に主翼に対して小間隔をおいてほぼ平行に装着
された小翼を設け、同小翼の主翼翼根側の前縁の
後退角が同小翼の主翼翼端側の前縁の後退角より
小さく設定されていることを特徴とする航空機の
主翼端渦減少装置。 A small wing is provided at the front of at least one of the upper and lower surfaces of the wing tip of the main wing, and is mounted approximately parallel to the main wing at a small distance, and the leading edge of the small wing on the root side of the main wing is set back. A main wing tip vortex reduction device for an aircraft, characterized in that the angle is set smaller than the sweepback angle of the leading edge on the wing tip side of the main wing of the small wing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP1987075208U JPH0454079Y2 (en) | 1987-05-21 | 1987-05-21 |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP1987075208U JPH0454079Y2 (en) | 1987-05-21 | 1987-05-21 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPS63184199U JPS63184199U (en) | 1988-11-28 |
| JPH0454079Y2 true JPH0454079Y2 (en) | 1992-12-18 |
Family
ID=30921136
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP1987075208U Expired JPH0454079Y2 (en) | 1987-05-21 | 1987-05-21 |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH0454079Y2 (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR20040040697A (en) * | 2002-11-07 | 2004-05-13 | 한국항공우주연구원 | Counter-rotating Twin Vortex Generator for Helicopter BVI Noise Reduction |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS5433498A (en) * | 1977-08-20 | 1979-03-12 | Masaaki Kusano | Method of producing high lift |
-
1987
- 1987-05-21 JP JP1987075208U patent/JPH0454079Y2/ja not_active Expired
Also Published As
| Publication number | Publication date |
|---|---|
| JPS63184199U (en) | 1988-11-28 |
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