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展向
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  spanwise
     For the transition process of flow field of a circular cylinder, recognize that it is evoked by the instability of ellipses in the vortex kernel, and this instability cause the motion of the vortex along spanwise, and streamwise coherent structures, and spanwise large-scale vortex broken up the small-scale vortex structures.
     在此基础上,研究了圆柱绕流流场的二维到三维的转捩过程,认为转捩过程是由于卡门涡脱落过程中涡核的椭圆不稳定性引起的,同时这种不稳定性也导致卡门涡街沿展向的波动,产生流向涡结构,并且随时间的发展,展向大涡结构在流场下游处破碎为小尺度涡结构,认为这时转捩过程发生。
短句来源
     SPANWISE EXTENDED EXPERIMENTAL STUDY ON THE LEBU TURBULENT DRAG REDUCTION
     LEBU湍流减阻的展向扩展实验研究
短句来源
     THROUGHFLOW NUMERICAL CALCULATIONS INCLUDING INFLUENCE OF SPANWISE MIXING IN A MULTISTAGE AXIAL FLOW COMPRESSOR
     计及气流展向掺混影响多级轴流压气机通流数值计算
短句来源
     A STUDY ON DISTURBANCES EVOLUTION IN SUPERSONIC MIXING LAYER WITH SPANWISE CURVATURE
     带展向曲率的超音速混合层中扰动演化的研究
短句来源
     Six rows of round holes were ungradatedly located at ±15°,±40° and ±60° from stagnation on the half cylinder leading edge. The holes in each row were spaced three hole diameters apart and were angled 30° and 90° to the surface in the spanwise and streamwise directions respectively.
     试件表面交错地开有 6排孔 ,以驻点为起点 ,位置分别在± 1 5°,± 4 0°及± 60°处 ,各排孔的孔间距均为 3个孔径 ,孔轴线与表面在展向及流向的夹角分别为 30°及 90°,孔长与孔径比为 4。
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  “展向”译为未确定词的双语例句
     The absolute instability of a cylinder wake has been studied experimentally by local heating in water channel.
     采用对圆柱展向局部电加热的方式,在水槽中实验研究了临界/亚临界雷诺数圆柱尾流的绝对不稳定性.
短句来源
     The spinning fan was represented as time-averaged momentum source terms distributed along the span of the fan with functional relationship to the local flow conditions in N-S equations.
     在分析中,旋转的螺桨被描绘成沿螺桨桨叶展向分布的、与本地流动参数相关的、时间平均的动量源项,通过在N-S方程中加入此动量源项来替代螺桨对流体的作用。
短句来源
     Using the parallel code of large-eddy simulation, three turbulence databases of turbulence elliptic jet are obtained, with Reynolds number is 15000 and grid numbers are 258×125×125 and the total volume size is 552GB. Based on the analysis of the spatio-temporal evolution of large-scale coherent structures of free jet, turbulent jets in crossflow with stream-wise and transverse elliptic nozzles, the basic vortical structures of turbulent elliptic jet are revealed.
     应用湍流大涡模拟方法得到Re数为15000、网格数为258×125×125、总容量达552GB的三个湍流椭圆射流数据库。 通过对自由射流、流向和展向椭圆喷嘴的湍流横向射流大尺度结构的时空演化进行分析,揭示了湍流椭圆射流的基本涡结构。
短句来源
     The Lagrange multipliers optimization method is presented for wing+winglet configuration with constraint for lifting coefficient and wing root bending moment. By shaping the wing with winglet,decrease the sum of induced drag and profile drag,increase span efficiency and lift-drag ratio.
     采用Lagrange乘数优化方法,约束升力系数和机翼翼根弯矩,通过修改机翼+翼梢小翼组合体的结构外形,减小机翼的诱导阻力和形状阻力,提高机翼的展向效率和升阻比的大小。
短句来源
     Research clarified the complex flow fields produced by SVGs.
     研究揭示了SVGs所产生的复杂流场,一是气流在SVGs台阶背风区形成展向回流流动,可用于火焰稳定;
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  相似匹配句对
     PV premiere Vision coming to China
     带着期待中国走来
短句来源
     Analysis of spanwise circulation for running wing piece
     转动翼板的环量分析
短句来源
     E-show
     e风采
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     E-exhibition
     E风采
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     Errors in Y axis
     Y偏差
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  spanwise
Supersonic gas flow over a semi-infinite plate with small harmonic spanwise disturbances
      
Spanwise propagation of turbulence in a boundary layer
      
The process of spanwise propagation of turbulence in a laminar boundary layer on a plate is numerically investigated.
      
Stability of a spanwise nonuniform boundary layer flow
      
The linear stability of a boundary layer flow with a spanwise-periodic nonuniformity in the velocity profile is investigated.
      
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The lift of a shallowly submerged rectangular hydrofoil is discussed in the paper.If the lift coefficient of airfoil is known as C_(L∞),then the lift coefficient of hydrofoil will be C_L=KC_(L∞).With a view to simplify the calculation,the method for calculating K is only discussed among calculation methods.Using this simple method in calculation and analysis,it is shown that the effect of gravity may be neglected under high speed condition,and both the chord length and the thickness of hydro- foil are factors...

The lift of a shallowly submerged rectangular hydrofoil is discussed in the paper.If the lift coefficient of airfoil is known as C_(L∞),then the lift coefficient of hydrofoil will be C_L=KC_(L∞).With a view to simplify the calculation,the method for calculating K is only discussed among calculation methods.Using this simple method in calculation and analysis,it is shown that the effect of gravity may be neglected under high speed condition,and both the chord length and the thickness of hydro- foil are factors to be considered.Then a method for calculating the lift of a shallowly submerged hydrofoil is obtained.The main assumption in deriving formula is as following:(1)The contribu- tion of upper and lower surface of hydrofoil to lift can be studied respectively.The contribution of upper surface to lift is influenced by free surface,while the contribution of lower surface to lift is not influenced by free surface.(2)The effect of gravity may be neglected when speed of hydro- foil is extremely high.The method of lifting surface is adopted in calculating free surface correc- tion factor K of upper surface.Having first confirmed in calculation that the π pattern chordwise vortex distribution has no contribution to K,it is only necessary to set up four π pattern vortices over chordwise in order to calculate K of upper surface of hydrofoil.Four projects were made to carry out tests on lift of hydrofoil of circular-back section. The results show that under shallowly submerged condition,the angle of attack at zero lift varies considerably with submergence.Then a method of correction for aspect ratio of hydrofoil is obtained.After correction of aspect ratio for test results,the nomogram for calculating the lift coefficient of rectangular hydrofoil of circular-back section of 0.06 and 0.1 relative thickness is made out.The result of these two hydro- foil thickness can also be used to calculate the lift of other hydrofoil thickness.

本文讨论浅浸矩形水翼升力的问题。如果已知机翼的升力系数 C_(L∞),则水翼的升力系数 C_L=KC_(L∞)。为了简化计算在计算方法中只讨论计算 K 的方法。文中首先用已有的简单方法进行了计算分析。结果表明在速度较高时可以忽略重力的影响,在浅浸深时弦长与翼厚都是必须考虑的因素。其次导出了浅浸矩形水翼升力的计算方法。导出公式的主要假定是(1)水翼上下表面对升力的贡献可以分别考虑。水翼上表面对升力的贡献受自由面影响,下表面对升力的贡献不受自由面影响。(2)水翼运动速度投高可以忽略重力的影响。在计算上表面的自由面修正因子 K 时,采用升力面方法。计算时首先论证了Π形涡沿展向分布对 K 没有贡献,在弦向只须布置四个Π形涡就足够。所以用布置在弦向的四个Π形涡来计算水翼上表面的 K。最后进行了相对厚度=0.1,展弦比 AR=6,10;=0.06,AR=4,6等四个方案圆背形剖面矩形水翼的升力试验。试验结果表明在浅浸深时零升力角随浸深有很大改变,并导出了水翼展弦比的修正方法。把试验结果经展弦比修正后制成计算=0.1与=0.06圆背形矩形水翼升力系数的诺莫图。计算其它厚度水翼的升力,可用上述二厚度水翼的结果线性...

本文讨论浅浸矩形水翼升力的问题。如果已知机翼的升力系数 C_(L∞),则水翼的升力系数 C_L=KC_(L∞)。为了简化计算在计算方法中只讨论计算 K 的方法。文中首先用已有的简单方法进行了计算分析。结果表明在速度较高时可以忽略重力的影响,在浅浸深时弦长与翼厚都是必须考虑的因素。其次导出了浅浸矩形水翼升力的计算方法。导出公式的主要假定是(1)水翼上下表面对升力的贡献可以分别考虑。水翼上表面对升力的贡献受自由面影响,下表面对升力的贡献不受自由面影响。(2)水翼运动速度投高可以忽略重力的影响。在计算上表面的自由面修正因子 K 时,采用升力面方法。计算时首先论证了Π形涡沿展向分布对 K 没有贡献,在弦向只须布置四个Π形涡就足够。所以用布置在弦向的四个Π形涡来计算水翼上表面的 K。最后进行了相对厚度=0.1,展弦比 AR=6,10;=0.06,AR=4,6等四个方案圆背形剖面矩形水翼的升力试验。试验结果表明在浅浸深时零升力角随浸深有很大改变,并导出了水翼展弦比的修正方法。把试验结果经展弦比修正后制成计算=0.1与=0.06圆背形矩形水翼升力系数的诺莫图。计算其它厚度水翼的升力,可用上述二厚度水翼的结果线性插入。

This Paper makes a brief review of the doublet method and horse-vortex method and also a detailed description of the Garner-Acum method by which a numerical calculation is made for five planforms of the wings. On the basis of the calculated results, this paper makes a further discussion on the ranges of the application of these methods.The Garper-Acum method is more suitable to the calculation of the lift interference correction for the sweptback wing because it takes into account the practical load distribution,...

This Paper makes a brief review of the doublet method and horse-vortex method and also a detailed description of the Garner-Acum method by which a numerical calculation is made for five planforms of the wings. On the basis of the calculated results, this paper makes a further discussion on the ranges of the application of these methods.The Garper-Acum method is more suitable to the calculation of the lift interference correction for the sweptback wing because it takes into account the practical load distribution, as wellas the nonuniformity in the spanwise and chordwise distribution of the induced upwash angle.

本文简单地回顾了偶极子法和单马蹄涡法,较详细地介绍了Garner-acum法,并用此法对五种机翼平面形进行了数值计算。在此基础上进一步探讨各种方法的适用范围。对于后掠机翼的洞壁升力干扰修正耒说,这几种方法中宜于选择Garner-acum法,因它既考虑到实际载荷分布情况,又考虑了诱导上洗角展向分布和弦向分布的不均匀。

In order to calculate the lifts of rectangular wings with different winglets at subsonic speeds, we have adopted the finite element method which divides spanwise lattice and determines spanwise locations of control points by means of a constant roll-angle method. The induced drags are also calculated by using combined flow field method.As the results of calculating various configuration of a winglet, we have found out some rules affecting the lift and drag characteristics of wings with winglets and picked out...

In order to calculate the lifts of rectangular wings with different winglets at subsonic speeds, we have adopted the finite element method which divides spanwise lattice and determines spanwise locations of control points by means of a constant roll-angle method. The induced drags are also calculated by using combined flow field method.As the results of calculating various configuration of a winglet, we have found out some rules affecting the lift and drag characteristics of wings with winglets and picked out a favourable configuration from them. The aerodynamic mechanism of winglets is also discussed.

本文采用的有限基本解方法,以等转角法划分展向网格和确定展向控制点位置。对带翼梢小翼亚音速矩形翼进行了升力计尊,并用联合流场法计算了诱导阻力。从各种方案的翼梢小翼计算中,找到了一些影响机翼升阻特性的规律和较佳方案,并对其机理作了分析。

 
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