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后缘
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  trailing edge
    Compared with symmetrical extraction algorithm and polygonal approximation algorithm, the algorithm can extract contour's typical character of the blade effectively, for example, leading edge and trailing edge.
    该方法与均匀取点法和多边形逼近法相比,能够有效地提取叶片轮廓中的典型特征部分(例如前缘和后缘),克服了传统算法丢失部分特征点的缺点; 同时有效地消除了数据冗余问题;
短句来源
    In this thesis, the control law based on adaptive filter for Smart Rotor with actively controlled trailing edge flap is researched.
    本文主要研究基于自适应滤波的主动控制后缘附翼智能旋翼控制律设计问题。
短句来源
    The work of this thesis is mainly about the design and test of an actuator for a smart rotor with the trailing edge configuration.
    本文对智能旋翼的研究主要是面向真实翼型的主动后缘襟翼智能旋翼驱动器模型设计和试验研究。
短句来源
    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.
    主动后缘附翼控制是一种较新的旋翼减振系统,它通过控制后缘附翼的偏转,调节桨叶的气动载荷,实现对机体激振力主要谐波分量的主动抵消。
短句来源
    In this paper, we mainly investigate trailing edge noise of the clean wing which is one of the most important airframe noise sources on an aircraft flying.
    而后缘噪声是干净机翼产生的主要噪声源。
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    Experimental Study on Active Trailing Flap Model
    主动控制后缘附翼模型的实验研究
短句来源
    Their availability, stability, and robustness are proved by simulation on both model rotor and real rotor with the effect of the design parameters of the flap studied.
    对模型与真实旋翼进行仿真计算并研究后缘附翼设计参数的影响,结果表明两种方法都具有较好的有效性、稳定性和鲁棒性。
短句来源
    Two step Roe scheme developed by Rogers was used to solve the artificial compressible INS equations,in order to simulate the laminar separation of the E387 airfoil near the tailing-edge at low Reynolds number(Re=6.0×10~4,1.0×10~5,2.0×10~6) and different angle-of-attack(α=0°,4°,7°),corresponding to the long laminar separation bubble.
    本文采用Rogers发展的双时间步Roe格式,求解拟压缩性修正不可压N-S方程。 数值模拟了低雷诺数条件下(Re=6.0×104,1.0×105,2.0×106),E387翼型在不同攻角条件下(α=0°、4°、7°)翼上表面后缘部分的层流分离现象,对应于长分离泡。
短句来源
    THE CALCULATION OF THE GROUND EFFECT ON THE SEPARATED FLOW OF AIRFOIL
    地面对带后缘分离翼型影响的计算
短句来源
    THE CALCULATION OF GROUND EFFECT ON THE FLOW ABOUT AN AIRFOIL WITH REAR SEPARATION
    地面对带后缘分离的翼型绕流影响的计算
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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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An investigation Was conducted to determine the effects of geometrical variables on longitudinal and lateral aerodynamic characteristics of parawings at low speed. The variables under study included variations in the shape of the trailing-edge,. the rib-strips, the apex angles, the strakes, the chord of the outer part of the wing, the shape of the keel, the slackness ratio, and the dihedral ange.The results of the study indicate that, for single keel two lobed parawing, the shape of the trailing-edge has a significant...

An investigation Was conducted to determine the effects of geometrical variables on longitudinal and lateral aerodynamic characteristics of parawings at low speed. The variables under study included variations in the shape of the trailing-edge,. the rib-strips, the apex angles, the strakes, the chord of the outer part of the wing, the shape of the keel, the slackness ratio, and the dihedral ange.The results of the study indicate that, for single keel two lobed parawing, the shape of the trailing-edge has a significant effect on the aerodynamic characteristics, the maximum lift-drag ratio with inward curved trailing edges can be much higher than that with straight trailing edges. Adding ribs to the flexible wing surface results in a decrease in drag and increase in lift-drag ratio . For parawings of higher apex angles , incresing the apex angle results in higher lift-drag ratio, and adding a small strake can increase the maximum lift coefficient and improve the stall characteristics. The lift characteristics can also be improved using a curved keel with proper curvature .Increasing slackness ratio exhibits a stabilizing increment in the directional stability Incresing the dihedral angle exhibits a stabilizing increment in the lateral stability, but contributes a destabilizing effect to the directional stability. within a certain range, the variation of the dihedral angle plays an inverse role on the lateral as well as the directional stability as that of the slackness ratio .

本文研究了伞翼几何参数变化对纵向与横侧气动特性的影响。在实验中改变的因素包括伞翼后缘形状,翼面上的肋条,伞翼顶角,边条小翼,外翼弦长,龙骨形状,伞翼的张开比和上反角。 研究结果表明,对于单龙骨双叶伞翼,后缘形状改变对气动特性有很大影响,采用向内弯曲的后缘与直后缘的情况相比,能使伞翼的最大升阻比提高很多。在翼面上加肋条,使伞翼的阻力减小、升阻比增大。对于顶角比较大的翼面,增加顶角将获得更大的升阻比。在这种翼面上加边条小翼,可使最大升力系数提高并且改善失速特性。采用适当弯曲的龙骨也使升力特性得到改进。 增加伞翼的张开比使航向静稳定度增大。增加伞翼的上反角使横向静稳定度增大,航向静稳定度减小。在一定范围内,改变上反角对横向和航向稳定性的影响与张开比的作用相反。

Many of the current fighter aircraft use maneuvering flaps to enhance air combat maneuverability. Based on wind tunnel tests, this paper deals with the ability and causes of maneuvering flaps to decrease drags, the effects of the flap span, the flap chord, the strake and the wing plane form on the aerodynamic characteristics of the maneuvering flap, the matching of leading-edge and tailing-edge flaps, the improvement in the large angle-of-attack flying quality. This study shows that maneuvering flap is an effective...

Many of the current fighter aircraft use maneuvering flaps to enhance air combat maneuverability. Based on wind tunnel tests, this paper deals with the ability and causes of maneuvering flaps to decrease drags, the effects of the flap span, the flap chord, the strake and the wing plane form on the aerodynamic characteristics of the maneuvering flap, the matching of leading-edge and tailing-edge flaps, the improvement in the large angle-of-attack flying quality. This study shows that maneuvering flap is an effective measure to improve air combat capability of fighter aircraft at large angles of attack. Maneuvering flaps can effectively control the flow Separation and decrease the drag at large angles of attack. They also can expand the buffet boundary and decrease the buffet intensity. As a result, the large angle-of-attack flying quality can be significantly improved by utilization of maneuvering flaps. To the end of optimum comprehensive effect, the effects on both the aircraft structure and the system must be taken into account during the choice of the parameters of maneuvering flaps.

机动襟翼是现代战斗机提高机动格斗能力的常用措施。本文根据风洞实验结果,讨论了机动襟翼减阻的能力和原因,襟翼弦长和展长的影响,前缘襟翼和后缘襟翼的配合使用问题,机翼边条和机翼平面形状对机动襟翼减阻的影响,以及机动襟翼对大迎角飞行品质的改善情况。讨论表明,机动襟翼是提高战斗机空战格斗能力的有效措施。它能控制气流分离和减小大迎角时的阻力,提高抖振边界和降低抖振强度,改善大迎角的飞行品质。为了得到最佳的综合效果,机动襟翼的参数选择必须考虑对飞机结构和系统的影响。

The three dimensional Navier-Stokes equation describing the recirculating flow field behind the trailing edge of the Barchan Dune vortex generator was solved numerically by the Artificial Damping and Compressibility Method. The structure and stability of the ox-horn shaped vortex scroll were analysed. Due to the arching effect and the pumping effect of the diverging sources at the tips, the Barchan Dune vortex serolls possess tenacious anti-disturbance property. Experimental results revealed that, compared with...

The three dimensional Navier-Stokes equation describing the recirculating flow field behind the trailing edge of the Barchan Dune vortex generator was solved numerically by the Artificial Damping and Compressibility Method. The structure and stability of the ox-horn shaped vortex scroll were analysed. Due to the arching effect and the pumping effect of the diverging sources at the tips, the Barchan Dune vortex serolls possess tenacious anti-disturbance property. Experimental results revealed that, compared with V-gutter at the same blockage ratio, the dragloss of the Barchan Dune vortex generator was reduced by 75-80%; the range of lean blow-out limits was extended to about 8 folds at the same inflow rate; and the ignition of combustible mixture was much easier. The experiments supported the diagnostic criterion for vortex stability proposed by Gao Ge in reference [1].

使用实验方法及数值求解三维Navier-Stokes方程,研究了模拟新月形沙丘的BD型旋涡发生器的后缘涡管气流结构及稳定特性.由于拱形效应及涡管尖端发散而产生的抽气作用,BD型涡管具有顽强的抗干扰性能。实验结果表明,和同样阻塞比的V型槽相比,BD型旋涡发生器的阻力下降75—80%,旋涡火焰的贫油稳定性得到大幅度扩展,并具有良好的点火性能.实验结果印证了作者在文献[1]中提出的提高旋涡稳定性的基本原则。

 
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