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   耗散格式 在 航空航天科学与工程 分类中 的翻译结果: 查询用时:0.557秒
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耗散格式
相关语句
  dissipation scheme
    Adaptive Delaunay Triangulation With Multidimensional Dissipation Scheme for High-Speed Compressible Flow Analysis
    用于高速可压缩流体分析的带多维耗散格式的自适应Delaunay三角剖分
短句来源
    The multidimensional dissipation scheme was developed and included in the upwinding algorithm for unstructured triangular meshes to improve the computed shock wave resolution.
    推导了多维耗散格式,并采用非结构化三角网格的迎风算法,改善了激波的计算结果.
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  dissipation scheme
With the help of a simple technique, the capability of the Jameson-Schmidt-Turkel numerical dissipation scheme has been enhanced to include hypersonic flows.
      
Due to the linear nature of the solutions with respect to x, a first order scalar dissipation scheme was used.
      
Figure 13 shows the results without applying a vorticity con nement, using the CUSP dissipation scheme.
      


The NND scheme presented by Prof.Zhang Han Xin of CARDC has been used in this paper to complete the following computa-tions: the two-dimensional inviscid flow around the symmetric plane of nosetip of space shuttle; the three-dimensional inviscid flow around the nosetip of space shuttle; the three-dimensional inviscid flow around axisymmetric indented body. Under the general coordinate system, the computation grids have been generated by algebra equations. The charac-teristic compatibitity equations have been...

The NND scheme presented by Prof.Zhang Han Xin of CARDC has been used in this paper to complete the following computa-tions: the two-dimensional inviscid flow around the symmetric plane of nosetip of space shuttle; the three-dimensional inviscid flow around the nosetip of space shuttle; the three-dimensional inviscid flow around axisymmetric indented body. Under the general coordinate system, the computation grids have been generated by algebra equations. The charac-teristic compatibitity equations have been used to treat the shock and body surface boundaries and there is a special treatment in translation of coordinate system. At last, the comparative computations have been completed using second order SCM scheme. The results of computation illustrate that the NND scheme used in this paper can avoid numerical oscillations and high resolution to shock-capturing.

本文采用气动中心张涵信教授提出的无波动、无自由参数耗散格式(NND)进行了如下的计算:航天飞机头部段对称剖面内的二维无粘绕流;航天飞机头部段三维无粘绕流;轴对称凹陷外形的三维无粘绕流。在物面坐标系下,用代数方程生成计算网格,利用特征相容关系式处理激波和物面边界。为了比较,还用SCM格式进行了计算。结果表明,本文所采用的NND格式,在捕捉流场内激波时不会出现非物理振荡,其收敛速度和所获得的计算结果都是令人满意的。

Based on the Boltzmann model equation, the unified simplified velocity distribution function equation describing microscopic molecular transport phenomena from various flow regimes can be presented by the aid of the basic characteristics on molecular movement and collision approaching to equilibrium. The discrete velocity ordinate technique is developed and applied to the distribution function equation in order to replace its continuous dependency on the velocity space, and then the equation will be cast into...

Based on the Boltzmann model equation, the unified simplified velocity distribution function equation describing microscopic molecular transport phenomena from various flow regimes can be presented by the aid of the basic characteristics on molecular movement and collision approaching to equilibrium. The discrete velocity ordinate technique is developed and applied to the distribution function equation in order to replace its continuous dependency on the velocity space, and then the equation will be cast into hyperbolic conservation law form with nonlinear source term. Drawing on the decoupling technique on molecular movement and collision in the DSMC method, the unsteady timesplitting method is used to split up the discrete distribution function equations into the colliding relaxation equations with the source term and the convective movement equations. The non-oscillatory, containing no free parameters, and dissipative (NND) scheme is employed to solve the convective terms and the colliding relaxation equation is numerically simulated by the aid of the secondorder RungeKutta method. The gas kinetic finite difference method for directly solving the molecular velocity distribution functions is established by the way of coupling and iteration. To improve the computational efficiency for various Mach number flows, three types of quadrature rules, such as the modified GaussHermite formula, the equally spaced threepoint composite NewtonCotes formula,are developed and applied to the discrete velocity space to evaluate the macroscopic flow parameters at each point in the physical space. As a result, a unified simplified gas kinetic algorithm has been developed for flows from rarefied transition to continuum. Based on analyzing the inner parallel degree of the unified algorithm, the parallel strategy adapted to the gas kinetic numerical algorithm is studied, and then the HPF (High Performance Fortran) parallel processing software for the unified algorithm is developed. To test the reliability of the present numerical method in solving the gas dynamical problems from rarefied flow to continuum, the onedimensional shocktube problems, the flows past twodimensional circular cylinder, and the threedimensional flows around sphere and spacecraft with various Knudsen numbers are simulated. The computations of one, two, and threedimensional flows indicate that both high resolution of the flow fields and good qualitative agreement with the theoretical, experimental, DSMC results can be obtained. The present method provides an economical and efficient way that the molecular velocity distribution function equation describing microscopic transport phenomena can be transformed into hyperbolic conservation equations to be solved with the finite difference method, and that the gas dynamical problems from rarefied flow to continuum can be reliably simulated.

通过引入碰撞松弛参数和当地平衡态分布函数对BGK模型方程进行修正,确定含流态控制参数的各流域均适用的气体分子速度分布函数简化控制方程。发展和应用离散速度坐标法于气体分子速度空间,利用一套在物理空间和时间上连续而在速度空间离散的分布函数来代替原分布函数对速度空间的连续依赖性。基于非定常时间分裂数值计算方法和无波动、无自由参数的NND耗散格式,建立直接求解气体分子速度分布函数的气体运动论有限差分数值方法。发展可用于速度空间宏观取矩的离散速度数值积分方法,获取物理空间各点的流动参数,由此发展一套能有效模拟各流域三维绕流问题的气体运动论统一算法。研究气体运动论数值算法所适合的并行方案,基于统一算法的HPF并行实现,建立一套能有效模拟不同流域复杂外形体绕流的HPF并行算法软件。通过对不同Knudsen数的一维、二维、三维气体绕流问题进行数值计算表明,计算结果与有关实验数据及其它途径得到的研究结果吻合较好,证实了本文发展的统一算法在求解稀薄流到连续流不同流域复杂绕流问题方面的可行性。

A high resolution numerical method is used to simulate multi-component flow problems based on the coupling Euler equations and non-conservative mass fraction equations. The new method prevents unphysical oscillations in the area of the contact discontinuity and ensures the positivity of the mass fraction. As numerical experiments, a Mach 1.22 air shock collapse of a helium bubble and an example in chemically reacting flows are simulated. Numerical results based on the fraction mass model are compared with results...

A high resolution numerical method is used to simulate multi-component flow problems based on the coupling Euler equations and non-conservative mass fraction equations. The new method prevents unphysical oscillations in the area of the contact discontinuity and ensures the positivity of the mass fraction. As numerical experiments, a Mach 1.22 air shock collapse of a helium bubble and an example in chemically reacting flows are simulated. Numerical results based on the fraction mass model are compared with results by non-oscillatory and non-free-parameter dissipation difference (NND) scheme and γ-model, results are satisfied.

把非守恒形式的体积分数方程与Euler方程组耦合,用交错中心型格式求解流体力学方程组。对一维情况下两种气体的相互作用和二维气泡的变形及塌陷问题进行了数值模拟,并把模拟结果与-γmodel方法和NND(Non-oscillatoryandnon-free-parameterdissipationdifferencescheme,无振荡无自由参数耗散)格式的模拟结果进行比较,达到了抑制界面两侧非物理振荡和保持体积分数正性的目的。

 
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