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无限插值
相关语句
  transfinite interpolation
     TRANSFINITE INTERPOLATION METHOD FOR 3-D GRID GENERATIONS
     无限插值方法生成三维网格
短句来源
     Based on the transfinite interpolation theory, an improved algebraic grid generation method has been developed by introducing the technologies, such as grid orthogonality control, surface normal vector control and weighted average smoothing, etc. This improved method overcomes some old shortages and greatly enhances the ability of computational grid generation. It is much applicable to the need of rapid grid generation in optimization design cycles.
     以无限插值理论为基础,通过引入网格正交控制、物面法向量控制、加权平均光顺措施,发展了一种改进的代数网格生成方法,克服了原来方法在网格生成方面的一些缺陷,有效改善了网格生成质量,大为提高了该方法的网格生成能力,网格生成速度极为迅速,非常适合于优化过程中计算网格的快速生成需要;
短句来源
  “无限插值”译为未确定词的双语例句
     The body-Fitted viscous moving mesh for unsteady flow is generated by algebraic finite integration. Then the steady and unsteady subsonic, transonic and supersonic viscous flows around airfoil and some aircraft are numerically simulated. The 3-dimensional unsteady Navier-Stokes equations are solved using the implicit LU-NND algorithm, with Baldwin-Lomax turbulent model.
     利用代数无限插值方法,生成适合非定常有粘流动计算用的贴体运动结构网格,从三维非定常Navier-Stokes方程组出发,采用LU-NND有限差分格式和Baldwin-Lomax湍流模型建立了一种数值模拟三维机翼和全机的亚、跨、超音速定常及非定常粘性绕流的计算方法和程序。
短句来源
     Based on the transfmite interpolation, The O-H type grids around the moving wing are generated. The calculated results show that the moving grid-strategy is feasible and effective.
     基于无限插值理论,采用广义无限插值生成了绕机翼的O-H型网格,计算结果表明,本文的网格生成方法可行、有效。
短句来源
     The in viscid flux is discretized by AUSM+ scheme. The viscid flux is discretized by second-order central difference scheme. Baldwin-Lomax turbulence model is implemented in Navier-Stokes flow solver.
     本文通过对AUSM+格式的应用研究,以Navier-Stokes/Euler方程为主控方程,利用无限插值理论生成结构网格,采用Baldwin-Lomax湍流模型,应用格心有限体积法,无粘通量项采用AUSM+格式离散,粘性通量项采用二阶中心差分格式离散,开发了跨音速定常、非定常流场解算器。
短句来源
     Three-dimensional structured grids of aircraft are constructed by commercial software GRIDGEN, and the body-fitted viscous moving grids are generated by algebraic finite integration and a kind of grid modified technology.
     使用商业软件GRIDGEN生成机翼、平尾、组合体以及T型尾翼的三维初始结构网格,用代数无限插值方法(TFI)和一种网格修正技术生成贴体的粘性运动结构网格。
短句来源
     A viscous grid around simple geometries is generated by the elliptic and algebraic method. Base on this initial grid, we can get the unsteady viscous grid by using TFI technique.
     本文采用代数方法和结合源项修正技术的偏微分方程方法生成高质量贴体结构化粘性网格,并以此作为初始网格,运用无限插值技术构造出适用于非定常流场求解的动态变形网格。
短句来源
更多       
  相似匹配句对
     SPLINE INTERPOLATING ON SEMI-INFINITE INTERVAL
     单边无限区间上的样条插值
短句来源
     Cubic -spline Interpolation at a Biinfinite Knot Sequence
     双边无限三次■—样条插值
短句来源
     REGION INTERPOLATION
     区域插值
短句来源
     RLH’s Interpolation
     RLH插值
短句来源
     Siemens AG Information & Communication Networks
     网络无限
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  transfinite interpolation
Transfinite interpolation on the medians of a triangle and best L1-approximation
      
A Transfinite Interpolation Method of Grid Generation Based on Multipoints
      
In this work two algebraic grid generation methods based on the Soni-linear and Soni-Hermite transfinite interpolation methods, respectively, are developed.
      
The necessary data of the transfinite interpolation formulas, such as coordinates and grid angles, are determined by more than one points along all the boundaries.
      
All grid systems described above were generated by using transfinite interpolation24,25 in the manner described in Refs.
      
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This paper presents a study of the transfinite interpolation grid-generation. The developed procedure is used to generate two dime-nsi onal grids around airfoils and three dimensional ones around wing-body configurations. As a noniterative method, it requires lesscomputational work, and can equally be applied to different grid topologies. The computational results show the effectiveness of the presentmethod.

本文研究了生成三维网格的无限插值理论,应用它构筑了绕翼身组合体的三维C-O型网格,这是一种代数方法,适用于不同拓扑结构的网格生成,具有程序编写简单、计算时间短的优点。在这种方法生成的网格上进行了二维与三维的数值实验,结果表明,它是一种有效的网格生成方法。

Presented here is a computational procedure for generating a mesh system and for solving the Euler equation for transonic flow around a wing and fuselage combination. In the first part, an algebraic procedure for the generation of boundaryfitted grids about wingfuselage configuration is presented. The grid has six exterior surfaces that map into a computational cube. It is first determined on the six boudary surfaces and then in the interior. Grid clustering technique is used to control the distribution of...

Presented here is a computational procedure for generating a mesh system and for solving the Euler equation for transonic flow around a wing and fuselage combination. In the first part, an algebraic procedure for the generation of boundaryfitted grids about wingfuselage configuration is presented. The grid has six exterior surfaces that map into a computational cube. It is first determined on the six boudary surfaces and then in the interior. Grid clustering technique is used to control the distribution of surface grids on the configuration, the twoboundary technique is used to determine the boundary surface grids that are not on the configuration, and transfinite interpolation is used to determine the interior grid. In order to control grid orthogonality to boundaries (both fuselage and wing surface), we include outward derivatives on certain boundary surfaces in transfinite interpolation. As an example, an O-C type grid for a model of wingfuselage configuration is generated. Secondly, an explicit timemarching finitevolume procedure solves the flow equation. The numerical results are in good agreement with experimental data (Fig.1).

采用代数方法中的广义无限插值法生成翼身组合体三维O-C型贴体网格。该方法使用双边界法和引入了物面外法向导数以保证物面附近网格正交的处理方法,提高了代数方法生成翼身组合体网格的质量。并用中心格式有限体积法求解跨声速EULER方程,以某翼身组合体模型为例,计算结果与实验符合良好。

The description of the moving grid\|strategy is presented. Based on transfinite interpolation, an O\|H type grid around one blade is generated. In each subdomain, the weighting funtion is given to account for the time\|variation of its nodes. The multi\|block grid modelling the whole rotor is achieved by the construction of grid\|blocks around each blade which are connected with coincident nodes on their common boundaries, the flowfield of a rotor is calculated by considering the transport of interface information....

The description of the moving grid\|strategy is presented. Based on transfinite interpolation, an O\|H type grid around one blade is generated. In each subdomain, the weighting funtion is given to account for the time\|variation of its nodes. The multi\|block grid modelling the whole rotor is achieved by the construction of grid\|blocks around each blade which are connected with coincident nodes on their common boundaries, the flowfield of a rotor is calculated by considering the transport of interface information. The calculated results show that the moving grid possesses feasibility and effectiveness. [

基于无限插值理论 ,将旋翼按桨叶数分为几个子块 ,然后在桨叶连续公共界面上对接各子块 ,形成绕整个旋翼流场的三维多块网格。各桨叶子块的流场信息直接通过连续公共界面相互交换 ,利用非定常欧拉方程求解出整个旋翼流场。发展的动态网格在前飞流场计算中取得了成功。

 
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