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  trailing edge
    For trailing edge problem,the integral equation of Kutta condition and the differential equation of vorticity conservation are solved simultaneously,and the vorticity distribution Υ(y)is found with t (time) and x (longitudinal location) as parameters.
    在后缘问题中联立求解了Kutta条件涡面积分方程和涡量守恒微分方程,得到了各个不同位置不同时问的旋涡分布,γ(y,x,t),因而比较清楚地阐明了后缘旋涡脱落和运动的机理以及非定常涡面的发展过程。
短句来源
    Water-tunnel experiment re- sults indicate that the reason for drag reducing of swept wing-tip is that when the angle of attack is not Zero,the strength tip vortex of the wing is weakened by the combined effect of the leading edge and trailing edge vortices of the swept wing-tip.
    水洞实验表明,后掠翼梢减阻的原因主要是在有迎角时,翼梢前缘涡和后缘涡共问作用削弱了翼梢涡,从而减小了飞机的诱导阻力。
短句来源
    Incompressible Reynolds averaged Navier Stokes equations are solved using pseudo compressibility method for the simulation of incompressible flow over a delta wing with trailing edge jet at high angles of attack. The Beam Warming implicit approximate factorization scheme and MML algebraic turbulence model are utilized in the simulation.
    本文用拟压缩性方法求解不可压流雷诺平均拟压缩N S方程组 ,对带有后缘喷流的三角翼粘性绕流进行了数值模拟 ,求解中采用了Beam -Warming隐式近似因子分解格式以及MML代数湍流模型。
短句来源
    In addition, the trailing edge jets may weaken or even eliminate the mixing phenomenon of the leading edge vortex, which is in advantage of the flight control of aircraft.
    另外 ,后缘喷流可以减弱乃至消除前缘涡混掺现象的发生 ,进而有利于飞行器的操纵 .
短句来源
    It also indicate that in the wake integration method,the location of wake integration surface should be set in the distance of 0.6~1.0 relative chord length from the trailing edge.
    尾迹面法中,尾迹面位置应处于离后缘相对弦长距离0.6~1.0之间.
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  posterior border
Head shaking was attenuated by the subcutaneous infiltration of the local anesthetic procaine into the posterior border of the external auditory meatus.
      
The posterior border consists of a nebulous field of labeling and occasional barrel-like structures.
      
The setae on the posterior border of the telson were used for grooming the maxillipeds and the anterior mouthparts.
      
An anterior increased density, that parallels the posterior border of the sternum, was noted on the lateral radiograph of two children who were at first thought to have an accessory diaphragm.
      
Inflammatory changes along the posterior border of the pad may also be used to help differentiate effusion from acute synovitis on unenhanced MR examinations.
      
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  posterior margin
characterized by the absence of eyes and by the presence of the spermatheca and sharp depression at the posterior margin of the thoracic metasternite.
      
dorsoporum in having an external seminal vesicle much shorter than the cirrus sac, a longer cirrus sac extending posteriorly to the level of the posterior margin of the ventral sucker and a pretesticular ovary; from N.
      
chaetodoni in having a smaller body size, symmetrical testes, a longer cirrus sac extending posteriorly to the level of the posterior margin of the ventral sucker and a trilobed ovary; and from N.
      
simentiensis differ in size and shape from those on the posterior margin of the haptor.
      
The structural correlate for DPL is a small clear patch of skin lying at the posterior margin of each opercular cavity.
      
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  posterior edge
On the anterior edge of pereionite 1 and the posterior edge of pereionite 5, specialized areas were found that allow penetration of the male's dactyli in the inter-segmental spaces of the female.
      
Using six cadaver knees, an isometric point was found 3?mm distal to the posterior edge of Blumensaat's line, at the 10:30-11:00 o'clock position in right knees, at the antero-proximal edge of the anatomic ACL attachment.
      
During both the upward and downward movements of the wing, its posterior edge lagged behind the anterior one, i.e.
      
Before penetrating the mussels, the worm first straddles the valves at the posterior edge of the shell and then, after having digested the posterior adductor muscle, removes and swallows the soft parts of the prey.
      
Smaller C4 and C5 tubules, located at the posterior edge, contained only relict oocytes.
      
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  trailing edge
The magnitude of this flow circulation is determined from the condition under which the flow leaves the trailing edge of the body (the analog of the Chaplygin-Zhukovskii postulate in potential flow).
      
We solve the problem of the natural oscillations of a gas flowing past a cascade of flat plates under the Joukowsky-Chaplygin condition that the velocity at the trailing edge of the profiles is finite.
      
The formation of a laminar wake in the flow behind a shock wave when the latter is shed from the trailing edge of a semi-infinite plate is investigated in this paper.
      
An analytic solution of the problem of the wake in the neighborhood of the trailing edge is obtained, from which it follows that, in contrast to [2], there is no line of singularities in the nonstationary boundary-layer equations in the flow domain.
      
This fact is also verified by the analysis of the flow in the neighborhood of a line of tagged particles leaving the trailing edge simultaneously with the shock wave.
      
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  其他


Lagrangian coordinates were introduced to investigate the unsteady boundary layer separation of elliptic cylinder at angle of attack. The; forward-movement of the separation point with time was calculated. As well as the first occurence of separation. It was. also found that the separation pattern would change, as expected, from rear-separation to fore-separation as the angle of attack increased.In respect to the numerical methodogy, coordinate transformations were introduced to map the nonuniform mesh points...

Lagrangian coordinates were introduced to investigate the unsteady boundary layer separation of elliptic cylinder at angle of attack. The; forward-movement of the separation point with time was calculated. As well as the first occurence of separation. It was. also found that the separation pattern would change, as expected, from rear-separation to fore-separation as the angle of attack increased.In respect to the numerical methodogy, coordinate transformations were introduced to map the nonuniform mesh points in the physical plane to the uniform mesh points in the auxialliary plane to simplify the finite difference formula, and the complicated moving-boundary problem was treated in a fixed-boundary manner.

本文引入拉格朗日边界层方程以研究突然起动的有攻角椭圆柱的分离问题,不仅计算了分离奇点的出现,而且计算了它们随时间的前移。计算也揭示了随着攻角的增大会由后缘分离变为前缘分离。在计算方法方面,本文引入变换将辅助平面上的均匀网格映射到物理平面上的非均匀网格,这样可以只在物理平面上需要提高精度的局部区域加密网格而不增加过多的计算时间,同时又能保留等距差分的简单、高精度的优点。此外,本文还将复杂的变边界问题(分离点前移)当作定边界问题处理而大大简化了程序。

Hummel's experiment on the rolling-up and interaction of the leading-edge and trailing-edge vortex sheets at slender delta wing is modeled numerically by a simple two-dimensional theory. The numerical results show that the trailing-edge vortex sheet will roll-up at the downstream of the wing, in the presence of the leading-edge vortex, and the direction of the circulation of the leading-edge vortex is oppsite to the trialing-edge vortex. The numerical results are in good agreement with the experiment. This work...

Hummel's experiment on the rolling-up and interaction of the leading-edge and trailing-edge vortex sheets at slender delta wing is modeled numerically by a simple two-dimensional theory. The numerical results show that the trailing-edge vortex sheet will roll-up at the downstream of the wing, in the presence of the leading-edge vortex, and the direction of the circulation of the leading-edge vortex is oppsite to the trialing-edge vortex. The numerical results are in good agreement with the experiment. This work is important to further understand o'f the downstream flow-field of a wing.

本文目的在于建立一个简单的二维理论模型,试图在电子计算机上数值地模拟出Hummel关于三角翼前缘涡和后缘涡层的卷起及其相互作用的实验结果。实验表明,在有前缘涡存在情况下,在后缘下游,后缘涡层也要卷起另外一个涡,而且前缘卷起的涡与后缘卷起的涡环量方向相反,所得计算结果与实验图象甚为相似。

The present paper deals with the slender body theory of flexible undulating lifting surface.The flows about leading edge problem,trailing edge problem and the second leading edge problem(i.e.the Ieading edge problem with oncoming vortices from upstream) are investigated respectively and as a result a unified solution is obtained.For trailing edge problem,the integral equation of Kutta condition and the differential equation of vorticity conservation are solved simultaneously,and the vorticity distribution Υ(y)is...

The present paper deals with the slender body theory of flexible undulating lifting surface.The flows about leading edge problem,trailing edge problem and the second leading edge problem(i.e.the Ieading edge problem with oncoming vortices from upstream) are investigated respectively and as a result a unified solution is obtained.For trailing edge problem,the integral equation of Kutta condition and the differential equation of vorticity conservation are solved simultaneously,and the vorticity distribution Υ(y)is found with t (time) and x (longitudinal location) as parameters.In the study of the second leading edge problem,the displacement effect of vortex sheet from the plane of symmetry is taken into account and thereby the difficulty of overlapping vortex sheet and the lifting surface is overcome.It can be shown that when the overlapping vortex sheet approaches close to the body surface infinitely,its effect on the flow vanishes.It is found that the hydrodynamic effect of a vortex sheet can be represented b y a single parameter denoted as W,which has the dimension of velocity and is a weighted average of vorticity induced velocity on the body surface.

本文讨论柔性非定常升力面的细长体理论。对于前缘问题,后缘问题和升力面外存在有旋涡的第二前缘问题的的流动作了分别的讨论,得出了统一的理论和流动的解。在后缘问题中联立求解了Kutta条件涡面积分方程和涡量守恒微分方程,得到了各个不同位置不同时问的旋涡分布,γ(y,x,t),因而比较清楚地阐明了后缘旋涡脱落和运动的机理以及非定常涡面的发展过程。对于第二前缘问题,考虑了涡面离开流动对称面的位移影响,并由此克服了涡面和物面重叠带来的困难。分析表明,当重叠部分的涡面无限接近物体(升力面)表面时,涡面的作用趋于消失。此外,在分析旋涡作用时发现,截面上涡面的流体动力效果可以由一个单一参数(记为W)来表示。W是有速度的量纲,物理上它是在物面上旋涡诱导速度的加权平均值。

 
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