翼型設計 的英文怎麼說

中文拼音 [xíngshè]
翼型設計 英文
two dimensional aerofoil design
  • : 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...
  • : Ⅰ動詞1 (設立; 布置) set up; establish; found 2 (籌劃) work out : 設計陷害 plot a frame up; fr...
  • : Ⅰ動詞1 (計算) count; compute; calculate; number 2 (設想; 打算) plan; plot Ⅱ名詞1 (測量或計算...
  • 設計 : devise; project; plan; design; excogitation; layout; layout work; styling
  1. As design studies progressed it was found that several airfoil shapes could be used to satisfy the new performance criteria.

    當進行的研究工作后,發現有幾種可以用來滿足新的性能指標。
  2. Multi - objective optimization of airfoils

    多目標氣動優化方法
  3. Manufactured and designed according to jb / t2603 - 94 standard, the product is a light and small crane hanged under the below of " 工 " type steel assisting with cd1 and md1 electronic calabash

    本產品是按jb / t2603 - 94標準製造的,與cd1和md1電動葫蘆配套使用,懸掛在工字鋼下的輕小起重機。
  4. This paper has focalized explosion suppression principle, and discussed possible effects on explosion suppression performances of expanded alloy, and stated possible bad effects on aircraft performances combined with explosion suppression design of wing integer fuel tank

    本論文著重討論了網狀鋁合金抑爆材料的抑爆機理,並分三個階段討論了可能影響抑爆性能的因素,同時結合某機整體燃油箱防爆,闡述抑爆材料裝填后可能對飛機性能造成的不利影響。
  5. Standard specification for design and performance of light sport gyroplane aircraft

    運動自轉旋機的和性能的標準規范
  6. Although aircraft designers and engineers continued to employ wing - warping techniques for years afterward ( especially on early monoplanes such as the bleriot xi ), ever faster flight speeds eventually led them to beef up wing structures to resist the resulting stresses

    雖然其後許多年間,飛機師和工程師仍繼續採用翹曲機(尤其是布雷修xi等早期單機) ,但由於飛行速度不斷提升,終于迫使他們加強機結構,以承擔所增加的應力。
  7. Variable diameter rotor is an effective method to improve the aerodynamic performance of tilt - rotor in both hover and cruise state. on the basis the research before, the variable diameter tilt rotor structure design has been finish, and in virtue of the technology of virtual prototyping to simulate and analyze the kinetic, dynamic and intensity property of it

    變直徑傾轉旋能有效的改善傾轉旋機懸停和巡航狀態下的氣動效率,本文提出了變直徑傾轉旋試驗模方案,完成了可變直徑傾轉旋的結構,並利用虛擬樣機技術對變直徑傾轉旋的運動特性、結構動力學特性以及結構強度進行了分析、研究。
  8. 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,從能量的角度入手,考慮干涉因子和阻力,提出了葉片翼型設計的一種新算方法。
  9. In this thesis, four types of steel beam - rectangular cfst column connections, including normal welded flange plate ( wfp ) connection, bolted flange plate ( bfp ) connection, stiffened end plate ( sep ) connection and double split - tee plate ( dst ) connection, were designed based on the configuration of steel frame connection. total 8 models, 2 models of each kind of connections were tested under low - reversed cyclic loading at the end of cfst columns. the relationships between force and displacement at the end of columns, the relationships between the moment and rotation of the joints, degradations of strength and stiffness, ductility, failure mechanism and failure characteristics of these four connections under different axial - compression ratios were presented

    本文借鑒鋼框架節點構造,了四種類矩形鋼管混凝土柱與鋼梁連接節點,包括常規栓焊( wfp )節點、緣全螺栓連接( bfp )節點、雙t板連接( dst )節點以及加勁端板連接( sep )節點,進行了四類節點8個模試件在柱端低周反復荷載作用下的抗震性能試驗研究,比較了不同軸壓比下節點的滯回性能、強度與剛度退化、延性、破壞機理與破壞特徵,主要結論有: 1 、節點的位移滯回曲線與轉角滯回曲線為塊分佈,沒有或略有捏攏現象,耗能能力強; 2 、軸壓比對節點滯回曲線有顯著影響,全部節點都有顯著的剛度退化; 3 、位移與轉角骨架曲線在峰值荷載後有較長的水平或下降段,具有良好的延性性能; 4 、從整體抗震性能上看,緣全螺栓連接節點、雙t板連接與加勁端板連接節點都優于常規栓焊節點,可在實際工程中加以推廣。
  10. First, the repeated structural analyses for static and dynamic characteristics are needed in the integrated optimization of composite wing structures. in this situation, the finite element model ( fem ) is time - consuming, while the continuum equivalent plate model ( epm ) is more efficient and often used

    首先,復合材料面結構綜合優化需要反復進行結構靜力和動力特性分析,如果採用有限元模( finiteelementmodel ,簡稱fem ) ,則其工作量太大。
  11. This article describes the development process of surrogate models and introduces some experiment design methods and approximation approaches that can be used for a mdo surrogate model, they are full factorial experiment design, orthogonal experiment design, uniform experiment design, central - composite experiment design, and polynomial response surface method, kriging method, radial basis function method and artificial neural network

    為此本文中分別介紹了正交試驗,均勻試驗以及中心復合試驗等幾種試驗方法,以及多項式響應面, kriging ,和徑向基函數等幾種數學近似方法。並且通過構造描述機展向升力分佈的代理模,對上述幾種方法作了對比分析。
  12. In this paper the direct iterative surface curvature ( disc ) design method is presented for designing airfoils at transonic speeds

    本論文採用直接表面曲率迭代方法( disc )進行跨聲速翼型設計
  13. Numerical results show that the method provides an effective tool for refining and designing a fransonic airfoil

    算例結果表明,本方法提供了一種跨音速及新翼型設計的有效工具。
  14. One possible use is in designing the shape of airplane wings

    一種可能性就是運用在機的造上。
  15. To put the method in some perspective, it helpful to briefly outline the two general approaches to airfoil design

    把一些觀點方法,它有助於扼要介紹兩個一般方式翼型設計
  16. In this regard, several airfoil templates are given based on existing designs, eg, the sd7037 airfoil and others

    在這方面,有幾個版本,基於現有翼型設計,例如, sd7037
  17. Nevertheless, a surprisingly wide variety of airfoils can be designed with just four segments

    然而,出乎意料的是各種各樣的翼型設計可以僅4部分
  18. Finally, a special form allows the user to prescribe any number of segments so that practical airfoils can be designed

    最後,一種特殊形式允許用戶指定任何數目的片段,可以使實際翼型設計
  19. 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、機形狀、匯流輸入檔案( phi2調整細節見下文) 、坐標送返展示
  20. The design method used here is relatively independent with the direct procedure of calculation of flow solver by finite volume method, other flow solvers can also be easily coupled with this design method

    本文的方法與正算過程有相對的獨立性,可分別和不同的流場分析程序耦合,形成翼型設計軟體。
分享友人