翼形形狀 的英文怎麼說

中文拼音 [yìxíngxíngzhuàng]
翼形形狀 英文
airfoil shape
  • 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...
  • 狀 : Ⅰ名詞1 （形狀） form; shape 2 （情況） state; condition; situation; circumstances 3 （陳述事件或...
  1. An aircraft ' s aerofoils are shaped so that air travelling over their top surfaces moves faster than that underneath, creating an area of low pressure

    一片小翼的形狀可以是通過它上方的氣流比通過它下方的氣流速度更快，從而產生下壓力。
  2. The company might not be willing to part with the motorola brand, its batwing logo or the patents that underlie the devices ' operations, design and manufacturing, some of which are used by other divisions at motorola

    該公司可能不願放棄摩托羅拉品牌，蝙蝠翼形狀的標識以及作為設備運作、設計和製造基礎的專利權，而摩托羅拉的其它一些部門也在使用這些。
  3. It is the key of ebfs, therefore, furthermore calculation about link are carried out in this thesis, introduced achieved research, summarized the affect of link on whole capability in the first, the second, numerical calculation are proceeded on link with ansys : with the purpose of discussing yielding mode critical length of link, established five different specimens ; with the purpose of discussing the influence of h / tw of web, b / tf of flange and h / b, established eighteen different specimens ; with the purpose of discussing the affect of stiffener, established four different specimens, and elaborated the affect of stiffener on link based on achieved test researches

    因此，本文對耗能梁段進行進一步計算分析，概述耗能梁段對整體性能的影響，並利用有限元程序ansys對耗能梁段進行數值計算：針對耗能梁段的屈服類型建立5種不同長度的模型，計算討論耗能梁段屈服類型的長度劃分；針對耗能梁段腹板高厚比、翼緣寬厚比以及梁段截面形狀等因素共建立了18種模型進行計算分析；針對加勁肋對耗能梁段的作用建立了4種模型，並結合已有的試驗闡述了加勁肋對耗能梁段的影響。
  4. From this compare, we can know that the lunate fin has higher efficiency than the rectangle fin

    為研究尾鰭的幾何形狀對水動力性能的影響，本論文選取了矩形翼和月牙形翼進行比較。
  5. It s commonly called " big bird " from the alignment of north and south wings widely spread from side to side. arrival lobby on the first floor, departure lobby on the second, you can also enjoy meals and shopping there

    機場終站如同在其左右安上翅膀，成張開羽翼的形狀，通稱為" bigbird " ， 1樓是到達大廳， 2樓是出發大廳，在那裡還可以品嘗美食和購物。
  6. The results show that the frame of the grid fin has the greatest effect on the grid fin drag characteristics, reducing the drag levels and enhancing the lift - drag ratio for grid fin may be obtained by selecting appropriate frame cross - section shape and thickness of grid fin

    計算結果顯示，格柵翼的幾何結構參數對格柵翼的氣動力特性影響很大，格柵翼的邊框剖面形狀和厚度對格柵翼的阻力影響最大，所以選擇合適的邊框厚度和剖面形狀可以有效地減少格柵翼的阻力，提高陞阻比。
  7. 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
  8. Abstract : the effects of airfoil geometric parameters on wing " s spacial and polarized scattering characteristics have been systematically revealed. the results of the study indicated that the calculating value of diffraction from trailing edge by using the formula of the straight wedge is very far from experimental results for vertical polarization, and the contribution of thickness of the trailing edge to scattering must be considered in the calculation. the scattering peak of leading edge depends only on radius of airfoil for horizontal polarization. but for vertical polarization, it depends on maximum thickness and the location of maximum thickness. engineering formulas for evaluating all scattering peaks were given in the paper. it is important for the design of low - rcs wing

    文摘:系統地揭示了翼形幾何參數對機翼的空間散射特性、極化散射特性的影響規律.研究發現，在垂直極化狀態下用理論尖劈公式計算機翼后緣繞射的計算結果與實驗結果相差甚遠.提出在垂直極化狀態下機翼后緣繞射的計算必須將后緣厚度考慮在內的見解.對於水平極化，前緣散射波峰只與前緣半徑有關；而對於垂直極化，前緣散射波峰與翼形最大厚度以及最大厚度位置有關.給出前後緣散射波峰的工程估算公式，為低雷達散射截面（ rcs ）機翼設計提供依據
  9. Compared with a delta wing aircraft, the double - delta wing configuration has better aerodynamic performance at high angles of attack. an operational analysis was introduced as a method for evaluating training effectiveness of trainer aircraft. approaches to the engineering estimation of aerodynamic characteristics for aircraft with a double - delta wing configuration were studied, and the procedures for determining aircraft performance indices formulated. taking training effectiveness as the objective function and geometric parameters of the wing platform as design variables, through a numerical multivariate optimization arithmetic, the conceptual design optimization for a certain fighter trainer aircraft with double - delta wing configuration was carried out under the constraints of tactical and technical requirements and interrelated geometry. agreement of a calculation example with engineering practice indicates that the optimal design has higher training effectiveness than the baseline design, and in addition, improves the structural force - bearing conditions

    雙三角翼氣動布局比三角翼飛機具有更好的大攻角空氣動力特性.引入了評估教練機訓練效能的作戰分析法，研究了雙三角機翼布局飛機空氣動力特性的工程計算途徑以及飛機性能指標的確定方法.以訓練效能作為目標函數並選取機翼平面形狀的幾何參數為設計變量，採用多變量數值尋優方法，在戰術技術指標及相關幾何約束條件下，對某高級教練機的雙三角機翼氣動布局方案進行了優化選擇.算例表明最優方案不僅比原準方案具有更高的訓練效能，還改善了結構的受力情況，與工程實踐吻合
  10. This paper studies the effect on aerodynamic characteristics of the grid fin geometry by choosing different cross - section shape and thickness outer frame, changing the thickness of internal fins and the density of internal honeycomb, comparing the datas obtained from the corresponding wind tunnel tests

    模擬了格柵翼的邊框剖面形狀和邊框厚度以及格柵莖厚度、蜂窩疏密度對格柵翼氣動力特性的影響，並把計算結果與實驗結果進行了比較。
  11. To study the acoustic unsteady combustion of srm, built the acoustic model of chamber. deduced the little amplitude sound wave 3d equation, used the finite volume discrete method to simulate. got the vibration model of three kinds of chamber

    為研究固體火箭發動機聲不穩定燃燒特性，建立了燃燒室內聲學特性分析的物理數學模型，推導了小振幅聲波三維波動方程，採用有限體積離散方法進行模擬，得到圓柱型、四片翼柱彤和五片翼柱型藥柱三種燃燒室形狀聲學振動基本模態
  12. In spite of these advantages, we should concentrate on how to extend the representation of modes, how to apply to unstructured grids, etc. and when combining pod and saa, it is necessary to know how to represent the shape and how to control the range of seeking and iteration number

    但在研究的過程中，我們發現正交分解方法也存在如下問題:如何增強基模態的表達能力，如何將該方法應用於非結構網格的計算等。在利用模擬退火演算法結合解算器進行翼型反設計時，則需要考慮如何表達幾何外形形狀，怎樣控制搜索范圍以及如何減小搜索次數等實際問題。
  13. This design has evolved from a previous version seen last year in japan, where the wave - like main profile formed part of a double - decker layout

    這個設計是從去年在日本所見到的版本中演變而來的，當時主風翼型面是呈波浪形狀的，組成了一個雙層風翼的布局。
  14. The results of test cases indicate that the flow parameters for the final design met the requirements and that the geometric parameters were fairly close to the desired values

    算例設計結果表明，最終設計翼型的流動參數和形狀參數都很接近要求的值。
  15. The new flap keeps essentially the same profile, but with a reduced cross sectional area at its extremities

    新副翼的形狀在總體上保持不變，不過在其末端的橫截面積卻變小了。
  16. The three basic steps are as follows : firstly, the flow field is computed. secondly, the droplet trajectory equation is solved in order to determinate the limiting droplet trajectories and local collection coefficient. thirdly, a new iced shape is defined according to ice accretion model

    其基本步驟一般分三步：計算物體的繞流流場；求解水滴軌跡方程以確定極限水滴軌跡和收集系數；根據冰增長模型來確定新的結冰翼型形狀。
  17. In the examples we get some evolution curves, such as the growth rates and shape functions, which are used to analyze the stability problems for the boundary layers of the fuselage and the wing

    算例給出了擾動幅值增長和形狀函數等演化曲線，並對機翼、機身的邊界層穩定性進行了分析和研究。
  18. 3. the characteristics of boundary layer ' s transition, shape and separation are researched. the details as follows : ( l ) airfoil surface is turbulent boundary layer flows ; ( 2 ) velocity figure changed unsteady near the point of boundary layer separation due to randomicity of turbulent flow ; ( 3 ) the airfoil have better state of boundary layer separation and poor stall characteristics because of the upper surface of airfoil is flat

    給出了該翼型的附面層特性：翼型表面基本為湍流附面層；在靠近附面層分離位置處，速度型形狀、特別是靠近翼型表面的底部速度型形狀變化不定，是湍流流動的隨機性所致；該翼型具有較好的附面層分離形態，但在失速迎角附近，附面層分離形態變化劇烈、失速特性差，是翼型上翼面形狀較為平坦所致。
  19. Experimental investigation for the effects of vectored trailing - edge jets on the leading - edge vortex reakdown of a double delta wing

    雙三角翼前緣剖面形狀對渦運動的影響
  20. After the airfoil is designed, the velocity distributions, airfoil shape, converged input file ( with phi2 adjusted, see details below ) and airfoil coordinates are returned for display

    翼型設計后的速度分佈、機翼形狀、匯流輸入檔案（ phi2調整細節見下文） 、翼型坐標送返展示
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