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   artificial dissipation 在 航空航天科学与工程 分类中 的翻译结果: 查询用时:0.183秒
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artificial dissipation
相关语句
  人工耗散
    In order to increase the computation efficiency, artificial dissipation, variable time step and enthalpy damping acceleration techniques are used in the five-step Runge-Kutta time stepping.
    在定常的计算中,采用5步Runge-Kutta时间推进,引进人工耗散,应用了当地时间步长、焓阻尼等加速收敛技术。
短句来源
    The cell-centered symmetric finite volume arithmetic and Runge-Kutta time stepping scheme are performed to solve Euler equation. The two order and four order artificial dissipation is introduced for stability, local time stepping and implicit residual smoothing technique is applied to save computer time.
    在求解Euler方程方面,采用格心格式的有限体积法进行空间离散,四步Runge-Kutta法作时间推进,二阶、四阶人工耗散作为稳定措施,还采用当地时间步长和隐式残值光顺提高收敛速度。
短句来源
    In order to prevent odd-even decoupling of the solution and oscillations near the shock waves, a blend of adaptive second- and fourth-order artificial dissipation is added.
    引入二阶与四阶相融合的自适应人工耗散项用以克服中心格式固有的奇偶不关联性和抑制激波附近解的震荡。
短句来源
    Ooscillating near the shock wave is eliminated by introducing artificial dissipation;
    引进人工耗散项以克服中心差分固有的奇偶不关联性和抑制激波附近解的振荡;
短句来源
  人工粘性
    The main numerical method of this code is coming from scheme (Jameson, Schimit and Turkel): using cell-centered finite volume method as spatial discretization tools, and a system of ordinary differential equations for time variable is obtained, which is solved by utilizing five-step Runge-Kutta scheme as time marching method , introducing artificial dissipation to damp high frequency oscillations near the shock and stagnation point.
    本论文采用欧拉方程作为控制方程,利用中心有限体积法进行空间离散,得到对时间变量的常微分方程组,采用龙格库塔多步法进行时间积分,加入人工粘性以消除激波和驻点附近的压力振荡等方法来对NACA0012翼型的实际流动进行并行数值模拟。
短句来源
    To ensure the numerical dissipation much smaller than the physical viscous terms, directional scaling of the artificial dissipation is achieved and proper boundary conditions are also introduced in this term.
    为保证高雷诺数下N-S方程的数值粘性远小于物理粘性,对人工粘性项进行了方向性修正并引入适当的边界条件。
短句来源
    The LU-ADI algorithm is employed in this paper, in order to control the numerical stability, the second-order and fourth-order artificial dissipation are added to the basic algorithm.
    采用LU-ADI格式计算,为提高格式的稳定性在隐式和显式部分分别添加了2阶和4阶人工粘性项。
短句来源
    Finite Volume Method (FVM) is used to calculate the 3-D viscous flow in the vectoring exhaust nozzle. The artificial dissipation and its boundary condition are improved to quicken the convergence and upgrade the precision of the numerical simulation.
    采用有限体积法计算了轴对称矢量喷管三维粘性流场,通过改进人工粘性及其边界条件提高了计算的收敛性和数值模拟的精度。
短句来源
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  artificial dissipation
In order to get smooth convergence for transonic, viscous flows, the artificial dissipation has been modified by using the time step for advective and diffusive equations.
      
A modified artificial dissipation based on the time-step limit for convective and diffusive equation has been used for numerical stability.
      
Only a fourth order artificial dissipation has been used here for global stability of the solution.
      
Artificial dissipation terms for finite difference approximations of linear hyperbolic problems with variable coefficients are determined such that an energy estimate and strict stability is obtained.
      
Conservative Finite Difference Formulations, Variable Coefficients, Energy Estimates and Artificial Dissipation
      
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Compressible flow around an NACA 0012 airfoil at high angle of attack is numerically simulated by solving the two-dimensional Navier-Stokes equations in a body-fitted system, the grid system is C-type grid generated algebraically. The LU-ADI algorithm is employed in this paper, in order to control the numerical stability, the second-order and fourth-order artificial dissipation are added to the basic algorithm. By using the Baldwin-Lomax turbulent model, the formation of the leading edge separation bubble,...

Compressible flow around an NACA 0012 airfoil at high angle of attack is numerically simulated by solving the two-dimensional Navier-Stokes equations in a body-fitted system, the grid system is C-type grid generated algebraically. The LU-ADI algorithm is employed in this paper, in order to control the numerical stability, the second-order and fourth-order artificial dissipation are added to the basic algorithm. By using the Baldwin-Lomax turbulent model, the formation of the leading edge separation bubble, as well as the convection of vortex along the airfoil surface and unsteady phenomena of vortex are simulated at high angle of attack. For some Mach numbers and angles of attack, the NACA 0012 airfoil turbulent solutions are periodie. By the comparison, the results in this paper agree with experiments and results received by other method.

以求解二维N-S方程数值模拟NACA 0012翼型大攻角状态的可压绕流特性;N-S方程是在贴体坐标系中给出的,以代数方法生成C型网格系统。采用LU-ADI格式计算,为提高格式的稳定性在隐式和显式部分分别添加了2阶和4阶人工粘性项。应用BaldwinLomax湍流二层代数模型模拟了大攻角时前缘分离涡的形成,旋涡对流及其非定常现象。在某些Mach数和攻角下NACA 0012翼型的湍流解具有周期性。通过比较,本文数值计算结果同实验及国外相应的数值计算结果基本吻合。

The new idea of making implicit scheme is developed on the basis of analyzing model equation inthis paper. By putting the above idea into Flux Vector Splitting, an Implicit Flux Vector Splitting(IFVS), which can avoid approximate factorization or block-bidiagonal, is provided to solve the timeaverage Navier-Stokes equations. A single-step three-node upwind difference scheme for vector fluxand central difference approximation for viscous terms are adapted.As a result,IFVS has no two-or-der numerical dissipation...

The new idea of making implicit scheme is developed on the basis of analyzing model equation inthis paper. By putting the above idea into Flux Vector Splitting, an Implicit Flux Vector Splitting(IFVS), which can avoid approximate factorization or block-bidiagonal, is provided to solve the timeaverage Navier-Stokes equations. A single-step three-node upwind difference scheme for vector fluxand central difference approximation for viscous terms are adapted.As a result,IFVS has no two-or-der numerical dissipation or artificial dissipation.It has obvious superiority in aspects of accuracy, robustness and little calculation.In the case of two-dimensional transonic cascade flows, shock wave exactly captured,and results are satisfied.

通过对模型方程的分析,给出了一种新的隐格式构造思想。将它运用到关通量分裂格式中,可得到无近似因子分解、无矩阵运算的高效二阶精度隐式矢通量分裂差分格式,并用来直接求解时间平均Navier-Stokes方程组。数值计算标明:该方法具有精度高、稳定性好、计算量少、收敛快等优点,在平面叶栅跨音流场的计算中,较好地捕获了激波,与实验比较,结果令人满意。

In this paper,three-dimensional Supersonic inlet flowfields have been calculated.The governing equations are nonsteady compressible Navier-Stokes equations. The discretization was Jameson's Runge-Kutta finite volume method. Modified Baldwin-Lomax algebraic eddyviscosity turbulent model and the wall function law were used. A new viscous terms discretization in the frame of finite volume method was adopted. For convergence acceleration,local time stepping,implicit residual average and artificial dissipation...

In this paper,three-dimensional Supersonic inlet flowfields have been calculated.The governing equations are nonsteady compressible Navier-Stokes equations. The discretization was Jameson's Runge-Kutta finite volume method. Modified Baldwin-Lomax algebraic eddyviscosity turbulent model and the wall function law were used. A new viscous terms discretization in the frame of finite volume method was adopted. For convergence acceleration,local time stepping,implicit residual average and artificial dissipation techniques were also used.A aircraft inlet flowfields of several flight states were calculated. The mean total pressure recovery and total pressure distortion across the engine face were obtained. These results were compared with experiment data and were proved to be satisfactory.

用Jameson的有限体积法,对某型号飞机在不同飞行状态下的进气道流场进行了数值模拟。求解的控制方程为三维非定常N-S方程。在对流项的计算上用二阶中心差分有限体积法,粘性项的计算则采用作者在[1]中发表的一种有限体积框架下的新的离散化技术,时间方向用多步Runge-Kutta方法进行推进,以增大CFL条件数。湍流模型则采用Baldwin-Lomax代数模型。求解过程中还采用了当地时间步长,隐式残量平均、人工粘性等加速收敛技巧。最后给出了各种飞行状态下进气逼出口截面的平均总压恢复与总压畸变,得出了比较满意的结果。

 
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