JPH04138994A - Air resistance reducing device - Google Patents
Air resistance reducing deviceInfo
- Publication number
- JPH04138994A JPH04138994A JP26044490A JP26044490A JPH04138994A JP H04138994 A JPH04138994 A JP H04138994A JP 26044490 A JP26044490 A JP 26044490A JP 26044490 A JP26044490 A JP 26044490A JP H04138994 A JPH04138994 A JP H04138994A
- Authority
- JP
- Japan
- Prior art keywords
- air resistance
- air flow
- air
- aircraft
- resistance
- 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
Links
- 230000001603 reducing effect Effects 0.000 title abstract description 14
- 230000000694 effects Effects 0.000 abstract description 9
- 239000007787 solid Substances 0.000 abstract 1
- 238000010586 diagram Methods 0.000 description 7
- 239000003292 glue Substances 0.000 description 6
- 238000009434 installation Methods 0.000 description 6
- 238000012423 maintenance Methods 0.000 description 5
- 230000000873 masking effect Effects 0.000 description 4
- 235000019592 roughness Nutrition 0.000 description 4
- 239000000463 material Substances 0.000 description 3
- 238000003801 milling Methods 0.000 description 3
- 238000007639 printing Methods 0.000 description 3
- 238000012545 processing Methods 0.000 description 3
- 239000000126 substance Substances 0.000 description 3
- 238000004519 manufacturing process Methods 0.000 description 2
- 238000003486 chemical etching Methods 0.000 description 1
- 238000012993 chemical processing Methods 0.000 description 1
- 239000004927 clay Substances 0.000 description 1
- 238000007796 conventional method Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000007598 dipping method Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000005530 etching Methods 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000003825 pressing Methods 0.000 description 1
Landscapes
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
Description
【発明の詳細な説明】 〔産業上の利用分野〕 本発明は航空機、飛しょう体、ロケット風洞。[Detailed description of the invention] [Industrial application field] The present invention relates to aircraft, flying objects, and rocket wind tunnels.
その他、可及的に小さい空気抵抗を求められる物体の空
気抵抗低減装置に関する。In addition, the present invention relates to an air resistance reduction device for an object that requires the smallest possible air resistance.
従来、航空機等では乱流境界層の摩擦抵抗を低減する目
的で、第９図に示すような気流方向に平行に７字型の溝
を持つリブレット１２を表面に装着している例が知られ
ている。Conventionally, for the purpose of reducing the frictional resistance of the turbulent boundary layer in aircraft, etc., it has been known that a riblet 12 having a 7-shaped groove parallel to the airflow direction is attached to the surface as shown in Fig. 9. ing.
上記従来のりブレットには解決すべき次の課題があった
。The above conventional glue bullet had the following problems to be solved.
即ち、航空機の摩擦抵抗は、巡航時全抵抗の約５０％と
大きなウェイトを占め、この抵抗低減は、輸送効率向上
に極めて大きく寄与する。That is, the frictional resistance of an aircraft accounts for approximately 50% of the total resistance during cruising, and reducing this resistance greatly contributes to improving transportation efficiency.
このため、数多くの研究、試行がなされており、リブレ
ットが有望な装置として実機に装着され、試験されてい
る。For this reason, numerous studies and trials have been conducted, and the libretto has been installed on actual machines and tested as a promising device.
しかしリブレットには、加工、装着、メンテナンスの費
用１期間が大という欠点があり、かつ気流方向がリブレ
ットの溝方向と１０’以上の角度を持つと、効果がなく
なり、巾広い迎角範囲で効果を保つ事ができないという
欠点がある。However, riblets have the disadvantage of high processing, installation, and maintenance costs per period, and if the airflow direction has an angle of 10' or more with the groove direction of the riblet, they become ineffective and are effective over a wide angle of attack range. The disadvantage is that it is not possible to maintain
本発明は上記従来のりブレットの欠点である加工、装着
を簡単、平明なものとし、費用、製作期間を減少すると
共に、気流の方向性の制約を取り除き、摩擦抵抗の減少
が可能な空気抵抗低減装置を提供することを目的とする
。The present invention simplifies processing and installation, which are the drawbacks of the conventional glue bullets, reduces costs and manufacturing time, and also reduces air resistance by removing constraints on the direction of airflow and reducing frictional resistance. The purpose is to provide equipment.
本発明は上記課題の解決手段として、可及的に小さい空
気抵抗を求められる物体において、同物体の空気流れに
接した面に相互に近接して設けられほぼ０．０５５ｍの
高さを有する多数の突起を具備してなることを特徴とす
る空気抵抗低減装置を提供しようとするものである。As a means of solving the above problem, the present invention provides an object in which air resistance is required to be as small as possible. An object of the present invention is to provide an air resistance reducing device characterized by comprising a protrusion.
〔作 用］
本発明は上記のように構成されるので次の作用を存する
。[Function] Since the present invention is configured as described above, it has the following function.
即ち、乱流境界層内の底部には、粘性底層と呼ばれる領
域があり、この粘性底層内におかれたＵ字形ノツチ、或
いは粗さ（突起）は第８図に示す如く、粘性底層内の縦
渦１１と呼ばれる渦の発達を、ノツチ或いは粗さ（突起
）によ′る渦の効果で抑え、これにより、縦渦１１を境
界層底層の低運動量流体域にとじこめ、境界層外層の高
運動量物体との混合を抑制して、壁近傍乱流境界層の運
動量増加を抑制し、これにより＊＊抵抗を低減する。That is, at the bottom of the turbulent boundary layer, there is a region called the viscous bottom layer, and the U-shaped notches or roughness (protrusions) placed in this viscous bottom layer are as shown in Figure 8. The development of vortices called longitudinal vortices 11 is suppressed by the vortex effect of notches or roughnesses (protrusions), thereby confining the longitudinal vortices 11 in a low momentum fluid region at the bottom of the boundary layer and increasing the height of the outer boundary layer. By suppressing mixing with momentum objects, the increase in momentum of the turbulent boundary layer near the wall is suppressed, thereby reducing drag.
従って本発明の構成の、物体の空気流れに接した面に相
互に近接して設けられた、はぼ０．０５ｍの高さの多数
の突起も全体として、物体表面の粗さを高めるため、上
記粗さと同様、物体の空気＊＊抵抗を低減する。Therefore, in the structure of the present invention, the large number of protrusions approximately 0.05 m in height that are provided close to each other on the surface of the object in contact with the air flow also increases the roughness of the surface of the object as a whole. Similar to the roughness mentioned above, it reduces the air** resistance of an object.
本発明の第１実施例を第１〜第５図により説明する。 A first embodiment of the present invention will be described with reference to FIGS. 1 to 5.
第１図は本実施例に係る外板を表面に備えた航空機の図
で、（ａ）は平面図、（ｂ）は（ａ）の側面図、第２図
は第１図に用いられた外板を拡大して示した模式的斜視
図で（ａ）は外板全体の図、Ｑ））は（ａ）の囲いｂの
拡大図、第３図〜第５図は一例として示した上記外板の
製作工程の説明図である。Figure 1 is a diagram of an aircraft equipped with the outer skin according to this embodiment on its surface, where (a) is a plan view, (b) is a side view of (a), and Figure 2 is the same figure used in Figure 1. In the schematic perspective view showing the outer panel enlarged, (a) is a view of the entire outer panel, Q)) is an enlarged view of enclosure b in (a), and Figures 3 to 5 are the above-mentioned views shown as examples. FIG. 3 is an explanatory diagram of the manufacturing process of the outer panel.
第１図において、１は航空機、２はその胴体。In Figure 1, 1 is an aircraft and 2 is its fuselage.
３は主翼、４は尾翼である。航空機１は空中を高速飛行
するので、可及的に小さい空気抵抗を求められるもので
、航空機１の空気流れと接する胴体２、主翼３２尾翼４
等の表面は本実施例の空気抵抗低減装置を備えた外板５
によって構成されている。3 is the main wing, and 4 is the tail. Since the aircraft 1 flies at high speed in the air, it is required to have as little air resistance as possible.
The surfaces of the above are the outer panels 5 equipped with the air resistance reducing device of this embodiment.
It is made up of.
外板５はその詳細を第２図に示すようにその表面に相互
の間隔（Ｄ）、約０．５ｍ、高さ（ｈ）、約０．０５■
の無数の突起６を備えており、後述する通り、航空Ｉ！
ｌの空気抵抗を著しく低減することができる。As shown in FIG. 2, the outer panel 5 has a mutual distance (D) of about 0.5 m and a height (h) of about 0.05 mm on its surface.
It is equipped with countless protrusions 6, and as described later, Aviation I!
The air resistance of 1 can be significantly reduced.
外板５の空気抵抗低減装置即ち、第２図により説明した
無数の突起６の製作はどのような工程によるも自由であ
るが、その−例を第３図〜第５図により説明する。Although the air resistance reducing device of the outer panel 5, that is, the countless protrusions 6 explained in FIG. 2, can be manufactured by any process, an example thereof will be explained with reference to FIGS. 3 to 5.
先ず、治具として第３図に示すようなプリント盤７を作
製する。プリント盤７には上記突起６に相当して間隔（
Ｄ）０．５ｍ、直径（ｄ）０．０５ｍ程度の柱状突起８
が無数に設けられている。この柱状突起８の先端にケミ
カル加工用のマスキング材９を着け、次いで第４図に示
すように航空機１の外板５の母材、即ちまだ突起６を施
されていない表面に、マスキング材９が当接するようプ
リント盤７を押しつけてマスキング材９を転写（マスキ
ング）する。この操作を繰返し、外板５の全表面を無数
の点状にマスキングした後、その裏面側は全面マスキン
グして第５図に示すようにケミカルエツチング用の溶液
１０内に外板５を約１時間浸積してエツチングし、マス
キングされた部分が上記突起６として残った外板５を得
る。従って、この場合は突起６の直径はほぼ０．０５ｍ
ないしはそれ以下となる。First, a printing board 7 as shown in FIG. 3 is prepared as a jig. The printed board 7 has an interval (
D) 0.5m, diameter (d) about 0.05m columnar projection 8
are provided in countless numbers. A masking material 9 for chemical processing is applied to the tip of the columnar projection 8, and then, as shown in FIG. The masking material 9 is transferred (masked) by pressing the printing board 7 so that the two are in contact with each other. After repeating this operation and masking the entire surface of the outer panel 5 in the form of countless dots, the back side is completely masked, and as shown in FIG. After time dipping and etching, the outer panel 5 is obtained with the masked portions remaining as the projections 6. Therefore, in this case, the diameter of the protrusion 6 is approximately 0.05 m.
or less.
次に本発明の第２実施例を第６図により説明する。本実
施例は空気抵抗低減装置を風洞の壁の内面（空気流より
見て表面）に施した例で、第６図は飛行機模型を内部に
備えた風洞の斜視的透視図である。図において２１は風
洞、２２は風洞の横壁。Next, a second embodiment of the present invention will be described with reference to FIG. This embodiment is an example in which the air resistance reducing device is applied to the inner surface of the wall of the wind tunnel (the surface seen from the air flow), and FIG. 6 is a perspective view of the wind tunnel equipped with an airplane model inside. In the figure, 21 is a wind tunnel, and 22 is a side wall of the wind tunnel.
２３は同じく土壁、２４は下壁で、それらの内面には図
示を省略した突起６が第２図の要領で施されている。但
し、本実施例の場合、横壁２２．上壁２３下壁２４はす
べて平面であるため、外板５の如く湾曲させる必要はな
い、従って、第３図で説明したプリント盤７を用いるに
しても湾曲の必要はない。Similarly, 23 is a clay wall, 24 is a lower wall, and projections 6 (not shown) are provided on their inner surfaces as shown in FIG. However, in the case of this embodiment, the side wall 22. Since the upper wall 23 and the lower wall 24 are all flat, they do not need to be curved like the outer panel 5. Therefore, even if the printed board 7 described in FIG. 3 is used, there is no need for them to be curved.
第７図は第１．第２実施例の空気抵抗低減装置、即ち、
第２図に示す構成の突起６と第９図に示す従来例のりブ
レット１２との空気抵抗低減効果の比較線図で、突起６
の高さｈを、摩擦速度ｖ１と。Figure 7 is 1. The air resistance reduction device of the second embodiment, that is,
This is a comparison diagram of the air resistance reduction effect between the protrusion 6 having the structure shown in FIG. 2 and the conventional glue bullet 12 shown in FIG.
The height h is the friction velocity v1.
動粘性係数νで無次元化した高さｈ＊ −ｖ １１・
ｈ／νが１０程度の時、滑面に対し、実施例の突起６で
は５％程度の空気抵抗低減効果があることを示している
。Height h* −v 11・dimensionless with kinematic viscosity coefficient ν
It is shown that when h/ν is about 10, the protrusion 6 of the example has an air resistance reducing effect of about 5% compared to a smooth surface.
なお民間輸送機が巡航している状態より、無次元高さｈ
”＝ｉｏに対応する突起の高さはｈΦ０．０５閣程度と
なる。In addition, from the state where a civilian transport aircraft is cruising, the non-dimensional height h
The height of the protrusion corresponding to "=io" is approximately hΦ0.05.
５％の抵抗低減は、航空機の輸送効率を直接５％高め、
燃料消費率を抑えると共に最大速度の面からは２．５％
の増加が可能である。航空機のような高度に洗練され、
かつ、あらゆる抵抗低減努力が払われた機体において、
更に５％程度の抵抗低減が得られる効果は画期的なもの
である。A 5% drag reduction directly increases aircraft transportation efficiency by 5%,
In addition to reducing fuel consumption rate, the maximum speed is reduced by 2.5%.
It is possible to increase Highly sophisticated, like an aircraft
And, in an aircraft in which every effort was made to reduce drag,
The effect of further reducing the resistance by about 5% is revolutionary.
また第２実施例の風洞の例では、駆動パワーの減少、或
いは最大速度の増加に効果がある。Further, in the wind tunnel example of the second embodiment, it is effective to reduce the driving power or increase the maximum speed.
以上の通り、第１．第２実施例によれば、航空機、風洞
等、可及的に空気抵抗の減少化を要求される対象物の空
気抵抗を著減できるという利点がある。As mentioned above, 1. According to the second embodiment, there is an advantage that the air resistance of objects such as airplanes and wind tunnels that require the reduction of air resistance as much as possible can be significantly reduced.
また、多数の突起は気流に対し、方向性を持たないので
、気流の向きに関係なく、常に抵抗低減の効果が得られ
るという利点がある。即ち、気流方向と１０°以上の角
度になると効果を失う従来例のりプレットに比し、全方
位に同等の効果が得られるという著しい利点がある。Further, since the many protrusions have no directionality with respect to the airflow, there is an advantage that the effect of reducing resistance can always be obtained regardless of the direction of the airflow. That is, compared to the conventional glue plate, which loses its effectiveness at an angle of 10 degrees or more with respect to the airflow direction, it has a significant advantage in that it can provide the same effect in all directions.
また、加工、装着、メンテナンスを必要とする従来例に
比し、第１．第２実施例の多数の突起はケミカルエツチ
ング（ケミカルミーリング）等で容易に得られ、かつ、
装着や格別のメンテナンスを必要としないという利点が
ある。In addition, compared to conventional examples that require processing, installation, and maintenance, The large number of protrusions in the second embodiment can be easily obtained by chemical etching (chemical milling), and
It has the advantage of not requiring installation or special maintenance.
本発明は上記のように構成されるので次の効果を有する
。Since the present invention is configured as described above, it has the following effects.
即ち、気流方向の如何に拘らず、空気抵抗を低減する装
置が得られる。That is, a device that reduces air resistance regardless of the direction of airflow can be obtained.
また、機械加工、装着、メンテナンス等を必要とした従
来例に比し、ケミカルミーリング等で容易に成形され、
かつ装着や、格別のメンテナンスを必要としない装置が
得られる。In addition, compared to conventional methods that required machining, installation, maintenance, etc., it can be easily formed using chemical milling, etc.
Moreover, a device that does not require installation or special maintenance can be obtained.
従って、きわめて低廉な装置かえられる。Therefore, the device can be replaced at a very low cost.
第１図は本発明の第１実施例に係る外板を備えた航空機
の図で（ａ）は平面図、 （ｂ）は側面図、第２図は第
１図に用いられる外板の詳細図で（ａ）は全体斜視図、
（ｂ）は（ａ）の囲いｂの拡大図、第３図は第２図に示
す外板の突起を成形するためのプリント盤（治具）の説
明図、第４図は第３図のプリント盤を用いて外板にマス
キング材を取付ける作業の説明図、第５図は第４図でマ
スキングした外板のケミカルミーリングの説明図、第６
図は本発明の第２実施例に係る風洞の斜視的透視図、第
７図は本発明の実施例の突起と従来例のリブレットとの
空気抵抗低減効果の比較線図、第８図は従来例のりプレ
ットによる摩擦抵抗低減の作用メカニズムの説明図、第
９図は従来例のりプレットの斜視図である。
ｌ・・・航空機。
４・・・尾翼。
２１・・・風洞。
２４・・・下壁。
３・・・主翼。
６・・・突起。
２３・・・土壁。
２・・・胴体。
５・・・外板。
２２・・・横壁。FIG. 1 is a diagram of an aircraft equipped with a skin panel according to a first embodiment of the present invention, in which (a) is a plan view, (b) is a side view, and FIG. 2 is a detail of the skin panel used in FIG. 1. In the figure, (a) is an overall perspective view,
(b) is an enlarged view of enclosure b in (a), Fig. 3 is an explanatory view of a printing board (jig) for forming the protrusion on the outer panel shown in Fig. 2, and Fig. 4 is an enlarged view of enclosure b in Fig. 3. An explanatory diagram of the work of attaching masking material to the outer panel using a printed board, Figure 5 is an explanatory diagram of chemical milling of the outer panel masked in Figure 4, and Figure 6
The figure is a perspective view of a wind tunnel according to the second embodiment of the present invention, FIG. 7 is a comparison diagram of the air resistance reduction effect between the protrusion of the embodiment of the present invention and the riblet of the conventional example, and FIG. 8 is the conventional example. FIG. 9 is an explanatory view of the working mechanism of frictional resistance reduction by the example glue plets, and is a perspective view of the conventional example glue plets. l...Aircraft. 4...Tail. 21...Wind tunnel. 24...Lower wall. 3... Main wing. 6... Protrusion. 23... Earthen wall. 2...Torso. 5... Outer board. 22...side wall.
Claims (1)
物体の空気流れに接した面に相互に近接して設けられほ
ぼ０．０５ｍｍの高さを有する多数の突起を具備してな
ることを特徴とする空気抵抗低減装置。An object that is required to have as low air resistance as possible is characterized by having a large number of protrusions with a height of approximately 0.05 mm that are provided close to each other on the surface of the object that is in contact with the air flow. Air resistance reduction device.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP26044490A JPH04138994A (en) | 1990-10-01 | 1990-10-01 | Air resistance reducing device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP26044490A JPH04138994A (en) | 1990-10-01 | 1990-10-01 | Air resistance reducing device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPH04138994A true JPH04138994A (en) | 1992-05-13 |
Family
ID=17348025
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP26044490A Pending JPH04138994A (en) | 1990-10-01 | 1990-10-01 | Air resistance reducing device |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH04138994A (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO1996008658A1 (en) * | 1994-09-16 | 1996-03-21 | Forschungszentrum Jülich GmbH | Device for breaking whirls at a surface submerged by a turbulent flow |
| WO1996008677A1 (en) * | 1994-09-14 | 1996-03-21 | Kvaerner Pulping Ab | Process for cleaning superheaters and other heat-transferring surfaces in recovery boilers |
| JP2013519591A (en) * | 2010-02-16 | 2013-05-30 | ザ・ボーイング・カンパニー | Aerodynamic structure with chevron solar panels and related methods |
| US9334045B2 (en) | 2008-02-29 | 2016-05-10 | Airbus Operations Limited | Aerodynamic structure with non-uniformly spaced shock bumps |
| US9463870B2 (en) | 2008-02-29 | 2016-10-11 | Airbus Operations Limited | Aerodynamic structure with series of shock bumps |
| US9896193B2 (en) | 2008-02-29 | 2018-02-20 | Airbus Operations Limited | Aerodynamic structure with asymmetrical shock bump |
-
1990
- 1990-10-01 JP JP26044490A patent/JPH04138994A/en active Pending
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO1996008677A1 (en) * | 1994-09-14 | 1996-03-21 | Kvaerner Pulping Ab | Process for cleaning superheaters and other heat-transferring surfaces in recovery boilers |
| WO1996008658A1 (en) * | 1994-09-16 | 1996-03-21 | Forschungszentrum Jülich GmbH | Device for breaking whirls at a surface submerged by a turbulent flow |
| US9334045B2 (en) | 2008-02-29 | 2016-05-10 | Airbus Operations Limited | Aerodynamic structure with non-uniformly spaced shock bumps |
| US9463870B2 (en) | 2008-02-29 | 2016-10-11 | Airbus Operations Limited | Aerodynamic structure with series of shock bumps |
| US9896193B2 (en) | 2008-02-29 | 2018-02-20 | Airbus Operations Limited | Aerodynamic structure with asymmetrical shock bump |
| JP2013519591A (en) * | 2010-02-16 | 2013-05-30 | ザ・ボーイング・カンパニー | Aerodynamic structure with chevron solar panels and related methods |
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