翼葉 的英文怎麼說

中文拼音 [yìyè]
翼葉 英文
winged petiole
  • 翼 : Ⅰ名詞1 （翅膀） the wing of a bird 2 （像翅膀的東西） the wing of an aeroplane etc : 鼻翼 wing of...
  1. A board on a paddle wheel

    明輪翼螺旋槳上的寬闊葉板
  2. Even the snaggy craggy oak - trees put out the softest young leaves, spreading thin, brown little wings like young bat - wings in the light

    甚至倔強嶙峋的橡樹，也發著最柔媚的嫩葉，伸展著纖纖的褐色的小枝翅，好象是些向陽的蝙蝠的翅翼。
  3. The seeds of 10 species ( 96 samples ) of the genus schisandra michaux were observed tinder light microscope and scanning election microscope. the results indicate " that : the macroslructural features of seed surface, including smooth type, rugulose type and tuberculate type, may suggest the evolutionary trend from smooth type to rugulose type, from rugulose type to tuberculate type ; the microstructural features of outer epidermis can be divided into two types, viz. verrucate type and reticulate type

    結果表明：該屬的種子宏觀形態呈現平滑、細皺紋或瘤狀突起，並認為五味子屬種子形態可能有從平滑到有細皺紋再到有瘤狀突起的演化趨勢；該屬種皮表面微觀形態可分為疣狀突起型（如：大花五味子、北五味子、東亞五味子、狹葉五味子、毛葉五味子、翼梗五味子和二色五味子）和網紋型（如：鐵箍散和重瓣味子） 。
  4. The two astazou turboprops are mounted in slender nacelles in the leading edges of the wings and drive three - blade propellers

    兩臺發動機安裝在機翼上小巧的發動機艙內，各驅動一個三葉螺旋槳。
  5. In order to analyze this model, a modified multi - blade coordinate transformation was proposed. at last, the aeromechanical stability problem was analyzed with the two

    最後用上述兩種分析方法對帶葉間減擺器的旋翼/機體耦合系統的氣動機械穩定性問題進行了分析研究。
  6. Proceed from the angle of energy and taking considerations on interference factor and drag of airfoil profile, a kind of new typed calculation method on the design of vane air foil was put forward according to the vortex aerodynamics model of the rotor of wind turbines with horizontal axis

    摘要根據水平軸風力機轉子的渦流氣動模型，從能量的角度入手，考慮干涉因子和翼型阻力，提出了葉片翼型設計的一種新型計算方法。
  7. The smart rotor with active trailing edge is a new system for reducing the vibration which can adjust the air load of the blade to actively counteract the main harmonic of the force to the fuselage by controlling the deflection of the trailing edge

    主動后緣附翼控制是一種較新的旋翼減振系統，它通過控制后緣附翼的偏轉，調節槳葉的氣動載荷，實現對機體激振力主要諧波分量的主動抵消。
  8. The dynamo runs at rull speed to drive main shaft, then the main shaft makes the emulsifying wings in emulsification grove rotate, which absorbs the liquid in its brand groove into ring groove through guide vanes on upper and lower sides of the groove. the vanes spins circularly at high speed with the main shatf as center, and the blade and emulsificaton groove cut and crush it continuously. after that. it gers squeezed by the vanes highspeed centrifugal rotation. at last, it finishes isotropt emulsification tratment within extremely short time after continuous circulating mixing

    由電動機全速運轉帶動主軸，經主軸轉動乳化框槽內之乳化翼片，使其將桶槽內之液體經框槽上、下兩側之導流葉片吸入環狀框槽內，經以主軸為中心高速圓周旋轉葉片；連續使乳化翼端刀面與乳化框間極小之間系高頻率之強力切割剪斷、粉碎，再借葉片高速離心旋轉排擠，持續循環混合，以極短之時間即可完成均質乳化之處理。
  9. Japanese snow crab leg, spicy seafood skewer, grill banana, skate wings with miso paste, charcoal grilled shrimp mousse on sugar cane

    ，還有特式日本松葉蟹爪香辣海鮮串炭燒香蕉西京燒魔鬼魚翼炭燒蔗蝦
  10. A part or surface, such as a wing, propeller blade, or rudder, whose shape and orientation control stability, direction, lift, thrust, or propulsion

    翼剖面；機翼；翼面一個部件或平面，如機翼、螺旋槳葉、方向舵等，其形狀或方位控制穩定性、方向、抬升、沖擊或驅動
  11. Within this analytical model, the factors as unsteady aerodynamic and blade flap / lead - lag coupled motion are both considered

    旋翼機體耦合動力學模型考慮了非定常空氣動力和槳葉揮舞擺振運動耦合。
  12. Frequency tests of helicopter rotating rotor blade

    直升機旋翼旋轉狀態下槳葉固有頻率的測試
  13. Numerical simulation of internal pressure fields in skew - swept impeller

    彎掠翼葉輪內流壓力場的計算機數值模擬
  14. Numerical simulation of internal secondary vortex in skew - swept impellers

    彎掠翼葉輪內流二次渦系的計算機數值模擬
  15. 2. an unsteady, nonlinear state - space airfoil aerodynamics model was developed with onera dynamic stall model

    對於後行槳葉的動態失速行為，引入了對翼型實驗數據不敏感，並也具有狀態空間形式的onera動態失速模型。
  16. In order to predict hydrodynamic characteristics a computational system is developed including determination of the pressure distribution on a wing section by use of the conformal mapping method and panel method respectively and of the flow in boundary layer according to the thin shear layer approximation ( tsl ) for navier - stokes equation approach. the wing sections of naca4412 and naca0012 are applied to test the computational system. the numerical inspection shows that the panel method with better precision and the momentum and the displacement thickness of boundary layer can be used to complete this calculation

    本文分別用守屋的保角變換法和基於源匯渦分佈的面元法，建立了計算槳葉表面壓力分佈的數學模型；應用納維-斯托克方程的薄層近似理論模式和有限差分數值方法，建立了計算機翼表面邊界層內部流動的數學模型；應用槳葉表面邊界層內部粘性流動和外部勢流流動在邊界上的匹配演算法，建立了槳葉表面二相流流動的計算方法和相應的計算機程序。
  17. The primary purpose of this paper is how to solve the overloaded propeller ' s condition. the style of propeller trailing edge cutting and shave on the pressure surface is adopted. the propeller ' s actual effect pitch will be reduced which cause the propeller ' s torque down

    本文主要是考慮螺旋槳出現負荷過重時如何處理的問題，所以採用槳葉隨邊切割並在葉面處將翼型修順的方式，實質上是切割后導致螺旋槳實效螺距的減小，從而使螺旋槳吸收的轉矩降低來達到主機負荷降低的目的。
  18. In addition, the dynamic equation of the rotor with trailing edges and the 2 - x actuator has been modeled for analyzing the aerodynamic performance of the rotor. the result of the analysis tells us that the performance of the rotor with trailing edges can get a remarkable improvement

    進而研究旋翼動力學模型，將推挽式雙x驅動器模型作為后緣附翼的一種驅動機構，分析旋翼的氣動性能，模擬運算結果表明，后緣附翼智能槳葉在各方面的性能都有顯著的提高。
  19. Main rotor blades were severed within the first few metres through contact with small trees and rocks, and the underbelly and right side of the fuselage were damaged substantially

    主旋翼槳葉在直升機沖前首數公尺處因碰觸地面矮小樹叢和石塊而斷裂，機腹和右側嚴重損毀。
  20. Lastly, previous vane are analysed by fluent, we calculate the pressure distribution chart and report chart of each wing form, then alter the torsion angle and the airfoil form of the vane respectively, finally ascertain the influence curve of the torsion angle and the airfoil form of the vane on which act the lift power

    最後，通過fluent對設計出的葉片分析，得出其壓力分布圖和報告圖。然後從改變葉片的扭轉角度和翼型兩個方面分析其對升力和阻力的影響。得出葉片的扭轉角和翼型對升阻比的影響曲線，在文章的結尾部分估算了無人機的一些性能參數。
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