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叶片后缘
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  “叶片后缘”译为未确定词的双语例句
     This paper presents and analyses the formation of air dynamical noise of mining axial fan briefly also, a discussion is given on the relationship between air dynamical noise and trailing track of following edge related to beundary—layer
     本文简要地介绍和分析了矿用轴流式通风机的空气动力噪声的形成,附面层及叶片后缘尾迹与空气动力噪声的关系。
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     An experimental equation about height of the Gurney flap and increment of lift coefficient of the airfoil is presented here.
     本文提出了 Gurney襟翼的高度与增升效果的经验公式 ,并提出了在轴流风机叶片后缘加装 Gurney襟翼从而提高风机的风量和风压的具体方法。
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     The socalled EM is named from spatial relationship (more precisely,phase angle relationship) between trailing edge and leading edge curves of two neighboring blade rows.
     缘线匹配是指相邻两叶排中前排叶片后缘线与后排叶片前缘线的空间关系,更准确地说是其相位角关系。
短句来源
     Moreover, with the increase of the height of blade tip clearance, the tip leakage flow is stronger and the origination position of the tip leakage vortex is closer to the trailing edge of the blade.
     此外,顶部间隙高度的增加,泄漏流动加强,旋涡的起始点更靠近叶片后缘
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     The result shows that both aerodynamic and aero acoustic performance of fan is best when the trailing edge of the blade keeps within the outlet plane of Diversion Cover.
     结果表明:当叶片后缘位于导流罩出口平面内时,风扇的气动性能和噪声指标均达到最佳。
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  相似匹配句对
     leaf>leafstalk.
     叶片>叶柄。
短句来源
     leaf> leafstalk.
     叶片>叶柄。
短句来源
     Precise description is the premise for turbine blade machining.
     对叶片后缘的精确建模是高质量加工的前提。
短句来源
     ANALYSIS ON THE INFLUENCE OF AERODYNAMIC PERFORMANCE ENLARGING THE AIRFOIL'S TRAILING EDGE THICKNESS
     增加风力机叶片翼型后缘厚度对气动性能的影响
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     ④Osteophyte formation of the vertebrae.
     4 )椎体后缘骨赘 ;
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  blade trailing edge
Heat transfer in passage with pin-fin arrays for cooling blade trailing edge was studied numerically.
      
The initial formation of the vortex is shown determined by the flow expansion angle while in yawed flows the developing vortex is then influenced by the vortex sheet shed from the inboard blade trailing edge.
      
The resulting processed flow fields reveal a significant increase in flow variability in a region relatively far downstream of the blade trailing edge, a phenomenon that is masked through the process of simple averaging.
      
Particle image velocimetry measurements were performed in phase with the propeller angle, to investigate the evolution of the axial and the radial velocity components, from the blade trailing edge up to two diameters downstream.
      
High resolution PIV measurements around a model turbine blade trailing edge film-cooling breakout
      
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The inverse mode of lag-entrainment method is used to predict both separated turbulent boundary layers and wakes, a new iteration technique suggested by Carter is applied to combine the inverse mode boundary layer calculation with a time marching in-viscid flow analysis. It is found that this technique is applicable to obtain a converge solution for separated cascade flow. For a high subsonic double-circular-arc axial compressor cascade the calculated Mach number distributions on the blades, downstream flow...

The inverse mode of lag-entrainment method is used to predict both separated turbulent boundary layers and wakes, a new iteration technique suggested by Carter is applied to combine the inverse mode boundary layer calculation with a time marching in-viscid flow analysis. It is found that this technique is applicable to obtain a converge solution for separated cascade flow. For a high subsonic double-circular-arc axial compressor cascade the calculated Mach number distributions on the blades, downstream flow angles and total pressure loss coefficients are in good agreement with experiment in the optimum incidence range. In the design incidence range the agreement between calculated results and experiment is not satistaetory.

本文给出一种计算压气机叶栅流场和气动性能的无粘流-边界层迭代方法.这种方法能够计算叶片后缘附近有紊流边界层分离的流动,考虑了尾迹对主流的位移效应.对一个高亚音速压气机叶栅的最小损失工况,计算得到的叶片型面M数分布、叶栅出口气流角、总压损失系数和试验值符合良好.

This paper presents and analyses the formation of air dynamical noise of mining axial fan briefly also, a discussion is given on the relationship between air dynamical noise and trailing track of following edge related to beundary—layer

本文简要地介绍和分析了矿用轴流式通风机的空气动力噪声的形成,附面层及叶片后缘尾迹与空气动力噪声的关系。

The cold flow in a sudden-expansion burner with a vane was viewed and surveyed preliminarily .Thirteen patterns of flow field are presented to discribe the effect of different vane trailing angles and different positions. The results show that with increasing of the vane trailing angle, the length of the recirculating flow and the total pressure loss rise. The distortion in the burner exit decreases.The method by using vane to control the flow field in a sudden-expansion burner is available.

对带有导流片的突扩燃烧室的冷态流场做了初步观察和测量。实验研究包括三个导流片的后缘角,纵向及横向位置各二个,共十三个结构的流场观测。研究结果表明:随叶片后缘角增加,回流区的长度明显减小,总压损失增加,而且叶片的位置和结构角对流场特征有一定的影响。因此,加导流片控制突扩燃烧室流场的方法是有希望的。

 
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