JPH0232000A - High-lift wing - Google Patents

High-lift wing

Info

Publication number
JPH0232000A
JPH0232000A JP63178202A JP17820288A JPH0232000A JP H0232000 A JPH0232000 A JP H0232000A JP 63178202 A JP63178202 A JP 63178202A JP 17820288 A JP17820288 A JP 17820288A JP H0232000 A JPH0232000 A JP H0232000A
Authority
JP
Japan
Prior art keywords
dents
flap
flow
wing
break away
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.)
Pending
Application number
JP63178202A
Other languages
Japanese (ja)
Inventor
Junichi Miyagawa
宮川　淳一
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.)
Mitsubishi Heavy Industries Ltd
Original Assignee
Mitsubishi Heavy Industries Ltd
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 Mitsubishi Heavy Industries Ltd filed Critical Mitsubishi Heavy Industries Ltd
Priority to JP63178202A priority Critical patent/JPH0232000A/en
Publication of JPH0232000A publication Critical patent/JPH0232000A/en
Pending legal-status Critical Current

Links

Classifications

    • 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
    • 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

Abstract

PURPOSE:To make it possible to generate lifting force without any break away until a large angle of incidence, by arranging many small dents on a wing surface, for generating vortex by dents and giving energy to a flow along a wing. CONSTITUTION:Plural lines of many small dents 3 are provided on the rear part of the upper surface of a flap 2 which extends backward from near the rear edge of a main wing 1, dents 3 are arranged on upper surface of the flap 2 in a way that plural number of dents 3a forming the first line from the front, plural number of dents 3b forming the second line,.... Dents in adjacent lines are shifted by a half pitch from each other and arranged in a zigzag. And by small vortexes generated by many dents 3, energy is given to the flow above the flap 2 and break away of the flow is prevented. Therefore, even when the angle of incidence of the flap 2 becomes big, break away of the flow is prevented from occurring and a high-lift can be obtained.

Description

【発明の詳細な説明】 〔竜業上の利用分野〕 本発明は、流体中を飛行する物体に大章造揚力を発生さ
せるための！（可動翼を含む、以下同じ）（で関する。[Detailed Description of the Invention] [Field of Industrial Application] The present invention is for generating a large lift force on an object flying in a fluid! (Including movable wings, the same applies hereinafter) (Regarding.

〔従来の技術〕[Conventional technology]

従来の技術として、通常の平滑面を持った翼がある。こ
れらは翼面上は平滑であり、凹凸は無かった。Conventional technology includes wings with normal smooth surfaces. These wing surfaces were smooth and had no irregularities.

〔発明が解決しようとする課題〕[Problem to be solved by the invention]

従来の平滑面を持った楓では、迎え角が大きくなると流
れが剥離し、それ以上の揚力を発生しなくなる。これは
翼面上で流れが急激な減速によりエネルギーを失うため
である。In conventional maples with smooth surfaces, when the angle of attack increases, the flow separates and no more lift is generated. This is because the flow on the wing loses energy due to rapid deceleration.

本発明は、流れの剥離を防止し、高い揚力をうろことが
できる翼を提供しようとするものである。The present invention aims to provide a wing that can prevent flow separation and provide high lift.

〔課題を解決するだめの手段〕[Failure to solve the problem]

本発明では、翼面上に多数の小さい窪みを配置した。 In the present invention, a large number of small depressions are arranged on the wing surface.

〔昨月〕[Last month]

本発明では、翼面上の小さい窪みの各々によって小さい
渦が発生し、翼面を沿う流れにエネルギーが与えられる
。このようにして、流体が、窪みの渦から受けるエネル
ギー人力により急激な減速にも耐え、大きな迎え角まで
剥離せずに翼面に沿って流れ、揚力を発生し続ける。In the present invention, each small depression on the wing surface generates a small vortex that imparts energy to the flow along the wing surface. In this way, the fluid can withstand rapid deceleration due to the energy input from the vortices in the depression, and continues to flow along the wing surface without separation even at large angles of attack, and continues to generate lift.

〔実施例〕〔Example〕

本発明の実施例を第１図及び第２図によって説明する。 Embodiments of the present invention will be described with reference to FIGS. 1 and 2.

本実施例では主翼１の後縁付近から後方に延びるフラッ
プ２の上面の後方部に複数例をなす多数の小さｈ窪み３
を設けている。In this embodiment, a large number of small h depressions 3 are formed in the rear part of the upper surface of the flap 2 extending rearward from near the trailing edge of the main wing 1.
has been established.

同窪み３は、第２図に示すように、前方より第一列を形
成する′Ｐ！！数の窪み３ａ、第二列を形成する複数の
窪み３ｂ、・・・・・・、としてフラッグ２の上面に配
置されている。As shown in FIG. 2, the depressions 3 form a first row from the front 'P! ! A number of depressions 3a, a plurality of depressions 3b forming a second row, . . . are arranged on the upper surface of the flag 2.

上記窪み３は、径３輔〜５闇、深さ１間〜２簡の半球状
であり、各列の窪みの間隔（Ｌ（第２図参照）は３期〜
５触の等ピッチとし、また互いに隣接する列の窪みは半
ピツチづつずらして千鳥状に配列されている。The recesses 3 are hemispherical with a diameter of 3 to 5 cm and a depth of 1 to 2 cm, and the interval (L (see Figure 2)) between the recesses in each row is 3 to
The pitches are equal to five, and the recesses in adjacent rows are staggered by a half pitch.

本゛実施例では、多数の窪み３によって発生する小さい
渦によってフラップ２上の流れにエネルギーが与えられ
、流れの剥離が防止される。In this embodiment, energy is imparted to the flow on the flap 2 by small vortices generated by the large number of depressions 3, and separation of the flow is prevented.

これによって、フラップ２の迎角が大きくなっても流れ
の剥離を起すことが防止され、高揚力をうろことができ
る。Thereby, even if the angle of attack of the flaps 2 becomes large, separation of the flow is prevented, and the high lift force can be maintained.

なお、上記実施例はフラップに窪みを設けているが、本
発明はこれに限られるものではなく、補助翼等の他の可
動翼、又は主翼等の固定翼等揚力を発生する＊に広く適
用することができる。Although the above embodiment has a recess in the flap, the present invention is not limited to this, and can be widely applied to other movable wings such as ailerons, or fixed wings such as main wings that generate lift. can do.

また、窪みの形状、大きさ、配列等も上記実施例に示し
たものに限られるものではなく、ま九窪みを翼上面の全
面又は前半部に設ける等窪みを設ける位置も流れの剥離
を防止する観点から適宜選定できることはいう迄もない
。In addition, the shape, size, arrangement, etc. of the depressions are not limited to those shown in the above embodiments, and the position where the depressions are provided can also prevent flow separation, such as providing the depressions on the entire surface or the front half of the upper surface of the blade. Needless to say, it can be selected as appropriate from the viewpoint of

〔発明の効果〕〔Effect of the invention〕

本発明は、翼面に配置された多数の小さか窪みによって
、翼面上の流れの剥離が防止され、太き々揚力を発生さ
せることができる。In the present invention, a large number of small depressions arranged on the wing surface prevent separation of flow on the wing surface, and it is possible to generate a large lift force.

【図面の簡単な説明】[Brief explanation of the drawing]

第１図は本発明の一実施例の斜視図、第２図はその要部
の拡大図である。FIG. 1 is a perspective view of an embodiment of the present invention, and FIG. 2 is an enlarged view of the main parts thereof.

Claims (1)

【特許請求の範囲】[Claims] 翼面上に多数の小さい窪みを配置したことを特徴とする
高揚力翼。A high-lift wing characterized by a large number of small depressions arranged on the wing surface.
JP63178202A 1988-07-19 1988-07-19 High-lift wing Pending JPH0232000A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
JP63178202A JPH0232000A (en) 1988-07-19 1988-07-19 High-lift wing

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP63178202A JPH0232000A (en) 1988-07-19 1988-07-19 High-lift wing

Publications (1)

Publication Number Publication Date
JPH0232000A true JPH0232000A (en) 1990-02-01

Family

ID=16044360

Family Applications (1)

Application Number Title Priority Date Filing Date
JP63178202A Pending JPH0232000A (en) 1988-07-19 1988-07-19 High-lift wing

Country Status (1)

Country Link
JP (1) JPH0232000A (en)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5540406A (en) * 1993-10-25 1996-07-30 Occhipinti; Anthony C. Hydrofoils and airfoils
JP2001354198A (en) * 2000-04-25 2001-12-25 Eads Airbus Gmbh Noise reducing device and eddy current generator for main wing of airplane
WO2007057155A1 (en) * 2005-11-15 2007-05-24 Airbus Deutschland Gmbh Brake flap for an aircraft
WO2010100237A2 (en) * 2009-03-06 2010-09-10 Vestas Wind Systems A/S A wind turbine providing increased power output
US8061652B2 (en) 2005-12-13 2011-11-22 Airbus Deutschland Gmbh Rudder of a commercial aircraft
US9638164B2 (en) 2013-10-31 2017-05-02 General Electric Company Chord extenders for a wind turbine rotor blade assembly

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5540406A (en) * 1993-10-25 1996-07-30 Occhipinti; Anthony C. Hydrofoils and airfoils
JP2001354198A (en) * 2000-04-25 2001-12-25 Eads Airbus Gmbh Noise reducing device and eddy current generator for main wing of airplane
WO2007057155A1 (en) * 2005-11-15 2007-05-24 Airbus Deutschland Gmbh Brake flap for an aircraft
JP2009515750A (en) * 2005-11-15 2009-04-16 エアバス・ドイチュラント・ゲーエムベーハー Aircraft brake flap
US8061652B2 (en) 2005-12-13 2011-11-22 Airbus Deutschland Gmbh Rudder of a commercial aircraft
JP4820878B2 (en) * 2005-12-13 2011-11-24 エアバス オペラツィオンス ゲゼルシャフト ミット ベシュレンクテル ハフツング Rudder for civil aircraft
WO2010100237A2 (en) * 2009-03-06 2010-09-10 Vestas Wind Systems A/S A wind turbine providing increased power output
WO2010100237A3 (en) * 2009-03-06 2011-07-14 Vestas Wind Systems A/S A wind turbine providing increased power output
US9638164B2 (en) 2013-10-31 2017-05-02 General Electric Company Chord extenders for a wind turbine rotor blade assembly

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