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数值耗散
相关语句
  numerical dissipation
    In order to reduce effectively the numerical dissipation of the rotor wake vorticity induced by Jameson's second-order cell-centered finite volume approach,with the combination of the third-order upwind scheme (MUSCL) and flux-difference splitting scheme,a numerical method based upon the solution of three-dimensional Reynolds-average N-S equations has been developed to simulate the flowfield around a lifting rotor in hovering.
    为减少Jameson二阶中心差分有限体积法导致的旋翼尾迹的数值耗散,将三阶逆风格式(MUSCL)与通量差分裂方法相结合,建立了一个三维雷诺平均N-S方程数值模拟悬停状态旋翼流场的方法。
短句来源
    The embedded grids methodology was adopted so as to weaken the numerical dissipation of the wake and be easy to apply the above mentioned boundary conditions.
    为进一步减少尾迹数值耗散和便于添加上述边界条件,采用了嵌套网格方法。
短句来源
    It is shown that the present method can effectively reduce the numerical dissipation of the rotor wake.
    计算结果表明,本文方法能够有效地减少旋翼尾迹的数值耗散
短句来源
    In order to consider effectively the effects of the rotor wake and reduce the false numerical dissipation of the rotor wake vorticity,a new hybrid method based on the Navier-Stokes/Free-Wake/Full-Potential solver has been developed for the efficient prediction of the three-dimensional flowfield of helicopter rotors.
    为充分考虑旋翼尾迹对流场的影响和减少尾迹的数值耗散,建立了一个基于Navier-Stokes方程/自由尾迹分析/全位势方程的旋翼流场求解的新的混合方法。
短句来源
    In order to reduce the false numerical dissipation of the rotor wake vorticity, a new hybrid method based on the Navier-Stokes/Free-Wake/Full-Potential solver has been developed for the efficient prediction of the rotor flowfield.
    为了减少旋翼尾迹的数值耗散,建立了一个基于Navier-Stokes方程/自由尾迹分析/全位势方程的旋翼流场求解的新的混合方法。
  “数值耗散”译为未确定词的双语例句
    MILES approach that replaced subgrid scale model by the intrinsic dissipation of preserving monotone schemes was accepted in the paper. Then, the possibility applied to LES of adapted schemes such as Harten-TVD scheme and MUSCL-TVD scheme was researched.
    本文采用MILES方法,认为保单调格式的数值耗散可以取代亚格子耗散,研究了Harten-TVD与MUSCL-TVD格式应用于LES的可能性。
短句来源
    Basing on the characteristics of the flows, the grid layout is designed properly and the parameters within entropy fix are adjusted carefully, so that the results are given further accurately.
    按照流场特点,合理地设计网格分布及调整不同黏性范围的熵修正,防止了壁面附近过大的数值耗散,使计算结果更加合理。
短句来源
    Embedded grids are adopted to weaken the numerical diffusion of the wake and to apply the above boundary conditions.
    为减少尾迹数值耗散和便于添加上述边界条件,采用了嵌套网格方法。
短句来源
    For the solution of NS equations the combination of the third-order upwind scheme(MUSCL) and flux-difference splitting scheme without adding artificial viscosity has been employed. As a result,the method can reduce the false dissipation of the rotor wake vorticity effectively when compared to Jameson's second-order cell-centered finite volume approach.
    在该模型中,将三阶逆风格式(MUSCL)与通量差分裂方法相结合,无需添加人工粘性,因而可有效地减少Jameson二阶中心差分有限体积法导致的旋翼尾迹数值耗散
短句来源
    To improve the accuracy in the simulation of rotor flowfield and noise in the CFD/Kirchhoff method,a combination of the third-order upwind scheme(MUSCL) and flux-difference splitting scheme,instead of the second-order center-difference scheme which may cause larger wake dissipation,is employed and a N-S solver based upon embedded grids is developed.
    将三阶迎风格式(MUSCL)与通量差分裂方法相结合,以改进二阶中心差分格式导致较大尾迹数值耗散的不足,建立了基于N-S方程和嵌套网格技术的旋翼流场求解方法,提高了CFD/Kirchhoff方法中流场信息计算的准确性.
短句来源
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  numerical dissipation
It has been well studied that the γ-function explicit method can be effective in providing favorable numerical dissipation for linear elastic systems.
      
It is also shown that this integration method provides favorable numerical dissipation not only for linear elastic systems but also for nonlinear systems.
      
Furthermore, the numerical dissipation of the method can be flexibly regulated, so that it is especially suitable for solving various discontinuity problems.
      
For different limiters, the different strength of numerical dissipation and dispersion of schemes is the reason why the schemes show obvious different characteristics.
      
After analysing and comparing the numerical dissipation and dispersion of various schemes, a new kind of limiter is proposed.
      
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A hyperbolic grid generation method based on upwind scheme has been developed. The inherent dissipation in this scheme can avoid the initial discontinuity propagating outward. Implicit scheme is adopted in the normal marching direction, so the choice of grid distance is arbitrary. In addition, an improved smoothing technique and a very effective method for the treatment of severe convex corner are presented. The robustness of the new scheme is demonstrated by grids generated for some typical configurations.

双曲型网格生成方法是一种十分适合于重叠网格方法应用的网格生成方法。为了避免双曲型方程将初始外形的不光滑性继续向外传播,本文采用了自动隐含数值耗散项的迎风格式进行数值离散。在法向推进方向,采用了隐式格式,使得网格推进步长的大小不受稳定性条件的限制。对实际应用中可能出现的边界条件进行了分类和处理。几个典型外形网格生成的质量是令人满意的,说明本文方法是成功的。

A numerical method for the simulation of two-dimensional super/hypersonic laminar flows in inlet is presented. The inflow Mach numbers are 4 and 6. The flowfields are simulated numerically by two-dimensional Navier-Stokes equations with two-order Roe’s scheme. Basing on the characteristics of the flows, the grid layout is designed properly and the parameters within entropy fix are adjusted carefully, so that the results are given further accurately. The shock waves at the compression corners are sharply resolved....

A numerical method for the simulation of two-dimensional super/hypersonic laminar flows in inlet is presented. The inflow Mach numbers are 4 and 6. The flowfields are simulated numerically by two-dimensional Navier-Stokes equations with two-order Roe’s scheme. Basing on the characteristics of the flows, the grid layout is designed properly and the parameters within entropy fix are adjusted carefully, so that the results are given further accurately. The shock waves at the compression corners are sharply resolved. The reflections and intersections of various shock waves in the inner of the intake and the separation flows induced by shock wave/boundary layer interaction are displayed reasonably. The comparisons of pressure distributions along the lip and ramp of another model computed by the present method with those by Keuk’s simulation and experiment show good agreement.

对超/高超声速三级压缩进气道流场进行了数值模拟,来流马赫数为4、6,进气道内流动为层流状态,根据二维Navier Stokes方程,采用二阶精度Roe格式进行离散。按照流场特点,合理地设计网格分布及调整不同黏性范围的熵修正,防止了壁面附近过大的数值耗散,使计算结果更加合理。在进气道模型的各级压缩折转角处,获得了清晰的激波结构,在进气道内部的各种波系的相交、反射和激波诱导的边界层分离等现象都得到合理的描述。计算得到的压力分布,在各级压缩斜板上同简单波理论结果十分接近。用本文方法计算了另一个二级压缩进气道,沿上、下壁面的压力分布与试验比较符合得较好。

In order to reduce effectively the numerical dissipation of the rotor wake vorticity induced by Jameson's second-order cell-centered finite volume approach,with the combination of the third-order upwind scheme (MUSCL) and flux-difference splitting scheme,a numerical method based upon the solution of three-dimensional Reynolds-average N-S equations has been developed to simulate the flowfield around a lifting rotor in hovering.To incorporate the important effects of the rotor wake,the far-field boundary condition...

In order to reduce effectively the numerical dissipation of the rotor wake vorticity induced by Jameson's second-order cell-centered finite volume approach,with the combination of the third-order upwind scheme (MUSCL) and flux-difference splitting scheme,a numerical method based upon the solution of three-dimensional Reynolds-average N-S equations has been developed to simulate the flowfield around a lifting rotor in hovering.To incorporate the important effects of the rotor wake,the far-field boundary condition derived from the rotor momentum theory and the cyclic boundary condition have been used.The embedded grids methodology was adopted so as to weaken the numerical dissipation of the wake and be easy to apply the above mentioned boundary conditions.Several cases of the blade surface pressure distribution have been calculated using the present method and the second-order center difference.The calculated results were validated by comparing with available experimental data.Then flowfield simulations under rotor hovering conditions were performed for three different blade tip planforms.The numerical results demonstrate that the swept tips can suppress supercritical flow.Additionally, the vorticity contours were computed and the characteristics of distorted rotor wake were analyzed.It is shown that the present method can effectively reduce the numerical dissipation of the rotor wake.

为减少Jameson二阶中心差分有限体积法导致的旋翼尾迹的数值耗散,将三阶逆风格式(MUSCL)与通量差分裂方法相结合,建立了一个三维雷诺平均N-S方程数值模拟悬停状态旋翼流场的方法。为了充分考虑旋翼尾迹对流场的影响,采用周期性边界条件和由动量理论导出的远场边界条件。为进一步减少尾迹数值耗散和便于添加上述边界条件,采用了嵌套网格方法。然后,进行了算例计算,给出了桨叶表面的压强分布,与可得到的试验数据及二阶中心差分方法的计算结果进行了对比,并针对几种不同桨尖形状的旋翼悬停流场进行计算,数值结果显示:后掠桨尖可减弱超临界流动。此外,还计算和分析了旋翼下方不同位置上的涡量分布。计算结果表明,本文方法能够有效地减少旋翼尾迹的数值耗散

 
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