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s形进气道
相关语句
  s-shaped inlet
    Numerical simulation of flow field for supersonic S-shaped inlet
    S形进气道流场数值模拟
短句来源
    Design and numerical investigation of dorsal S-shaped inlet
    背负式S形进气道设计及数值分析
短句来源
    According to the layout characteristics of UAV(unmanned air vehicle) platform,a dorsal subsonic S-shaped inlet with short diffuser and large offset is designed.
    针对无人机布局特点,设计了一种短扩压、大偏距、背负式S形进气道
短句来源
    By using CFD software flow characteristics of S-shaped inlet are analyzed. Furthermore,the effect of fuselage on the inlet by means of the angle of attack is given.
    利用计算流体力学(CFD)方法分析了S形进气道的内流特性及机身对S形进气道性能的影响。
短句来源
    Test under takeoff condition is designed to verify the inlet performance. The results show that the S-shaped inlet has good performance and the design project meets the design requirements primarily.
    此外,作为验证,进行了进气道与发动机的地面试验,数值计算与试验结果都表明,S形进气道具有较好的气动特性,有一定工程应用价值。
短句来源
  s-shaped inlet
    Numerical simulation of flow field for supersonic S-shaped inlet
    S形进气道流场数值模拟
短句来源
    Design and numerical investigation of dorsal S-shaped inlet
    背负式S形进气道设计及数值分析
短句来源
    According to the layout characteristics of UAV(unmanned air vehicle) platform,a dorsal subsonic S-shaped inlet with short diffuser and large offset is designed.
    针对无人机布局特点,设计了一种短扩压、大偏距、背负式S形进气道
短句来源
    By using CFD software flow characteristics of S-shaped inlet are analyzed. Furthermore,the effect of fuselage on the inlet by means of the angle of attack is given.
    利用计算流体力学(CFD)方法分析了S形进气道的内流特性及机身对S形进气道性能的影响。
短句来源
    Test under takeoff condition is designed to verify the inlet performance. The results show that the S-shaped inlet has good performance and the design project meets the design requirements primarily.
    此外,作为验证,进行了进气道与发动机的地面试验,数值计算与试验结果都表明,S形进气道具有较好的气动特性,有一定工程应用价值。
短句来源
  “s形进气道+”译为未确定词的双语例句
    AN INVESTIGATION ON FLOW BEHAVIOUR IN AN S-SHAPED DUCT
    实用S形进气道内部流动特性研究
短句来源
    Serpentine Inlet Performance Enhancement Using Vortex Generator Based Flow Control
    一种双S形进气道流场特性及控制的试验研究(英文)
短句来源
    The computational results of the Poissuill flow and the Couette flow are in a good agreement with analysis solutions and the comparison between experimental results and the numerical solutions of the internal flow in a S-shaped duct is satisfactory.
    二维Poissuill流动和Couette流动的计算结果和精确解吻合良好。 S形进气道的数值解反映出的现象和实验结果是一致的。
短句来源
    Outer flow of the inlet was computed in consideration of inner flow.
    考虑了外流场对进气道内部气流流动状况的影响,将S形进气道的内外流场进行综合求解。
短句来源
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Based on the Beam-Warming scheme, the flux-splitting method and the block-line-Gauss-Seidel technique, an implicit finite difference method with the second-order accuracy is developed for the numerical solutions of the compressible Navier-Stokes equations in a general curvilinear coordinate system. The algorithm can remldy the errors caused by the approximate factorization and deal with the viscous terms reasonably. The computational results of the Poissuill flow and the Couette flow are in a good agreement...

Based on the Beam-Warming scheme, the flux-splitting method and the block-line-Gauss-Seidel technique, an implicit finite difference method with the second-order accuracy is developed for the numerical solutions of the compressible Navier-Stokes equations in a general curvilinear coordinate system. The algorithm can remldy the errors caused by the approximate factorization and deal with the viscous terms reasonably. The computational results of the Poissuill flow and the Couette flow are in a good agreement with analysis solutions and the comparison between experimental results and the numerical solutions of the internal flow in a S-shaped duct is satisfactory.

本文在Beam-Warming格式的基础上,引入通量分裂的概念,应用行高斯迭代技术提出了一个二阶隐式的求解BFC坐标变换下的N-S方程的增量迭代法。它消除了因式分解带来的寄生误差,合理地处理了控制方程中的粘性项,具有较好的收敛性和稳定性。二维Poissuill流动和Couette流动的计算结果和精确解吻合良好。S形进气道的数值解反映出的现象和实验结果是一致的。

A new efficient finite-difference scheme for solving turbulence K-ε equations-Turbulence U-scheme has been developed.This method was combined with the solver of Navier-Stokes discreted by a modified Beam-Warming scheme to investigate three-dimensional turbulent internal flow in S-shaped duct.Many numerical experiments and practical applications show that this method provides detailed flow field and parameters for engineering design.As a special example,a numerical simulation has been completed for an S-shaped...

A new efficient finite-difference scheme for solving turbulence K-ε equations-Turbulence U-scheme has been developed.This method was combined with the solver of Navier-Stokes discreted by a modified Beam-Warming scheme to investigate three-dimensional turbulent internal flow in S-shaped duct.Many numerical experiments and practical applications show that this method provides detailed flow field and parameters for engineering design.As a special example,a numerical simulation has been completed for an S-shaped duct including separation,secondary flow,vortices etc.The comparison of its results with the flow patterns in the circular section s-shaped duct shows a good agreement in essence.

根据YangJY的思想构造了一种求解湍流k-ε模型方程的有限差分格式—湍流U-格式。采用此种方法以及一种完全N-S方程解算器对变截面S形弯曲进气道内部旋涡湍流运动进行了研究,通过大量型号设计与计算证明了本套方法可以正确地描述流场中的分离、二次旋涡等重要物理现象。作为一种特例,本文给出了一种S形进气道内部流动的数值模拟结果,并与圆截面S形弯管的计算结果进行了定性比较。

According to the layout characteristics of UAV(unmanned air vehicle) platform,a dorsal subsonic S-shaped inlet with short diffuser and large offset is designed.In the process of the design,two curved surfaces are intersected to make the scarf lip which the thickness varies;new center line and area regularity(duct curvature and cross section) are created.By using CFD software flow characteristics of S-shaped inlet are analyzed.Furthermore,the effect of fuselage on the inlet by means of the angle of attack is...

According to the layout characteristics of UAV(unmanned air vehicle) platform,a dorsal subsonic S-shaped inlet with short diffuser and large offset is designed.In the process of the design,two curved surfaces are intersected to make the scarf lip which the thickness varies;new center line and area regularity(duct curvature and cross section) are created.By using CFD software flow characteristics of S-shaped inlet are analyzed.Furthermore,the effect of fuselage on the inlet by means of the angle of attack is given.Test under takeoff condition is designed to verify the inlet performance.The results show that the S-shaped inlet has good performance and the design project meets the design requirements primarily.

针对无人机布局特点,设计了一种短扩压、大偏距、背负式S形进气道。设计中采用变厚度唇口技术,两曲面相贯构造斜切进口技术,并对前人提出的扩压器中心线方程和面积变化规律进行了改进。利用计算流体力学(CFD)方法分析了S形进气道的内流特性及机身对S形进气道性能的影响。此外,作为验证,进行了进气道与发动机的地面试验,数值计算与试验结果都表明,S形进气道具有较好的气动特性,有一定工程应用价值。

 
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