Global one - dimensional finite volume euler equations coupled with chemical reactions are implicitly solved to simulate the reacting flowfield of the combustor of scramjet fueled by hydrogen or hydrocarbon 本文采用隐式格式强耦合求解有限体积法离散的考虑化学反应的广义一维euler方程,数值模拟氢或碳氢燃料超燃冲压发动机燃烧室的化学反应流场。
The numerical examples presented here are representative test cases of the aerodynamics problems which contains shock and complicated flow structures . the solutions of euler equations for these examples certify the advantages of eno schemes 文中选取了具有代表性的算例,通过求解euler方程来验证eno格式在处理包含激波和复杂流动结构的空气动力学问题中所具有的优点。
The cell - centred finite volume algorithm , nnd finite volume algorithm and ausm + finite volume algorithm are studied for solving the euler equations , their abilities for hypersonic problem are studied especially 本文分别对格心有限体积格式、 nnd有限体积格式和ausm +有限体积格式进行了研究,在求解euler方程的基础上,研究了它们对跨音速以及高超声速流场计算问题的解决能力。
4 ) the euler equation is solved for the combination of wingbody by means of the finite volume method on the unstructured grids . several methods are used for quick convergence and the results are in correspondence with the experiment data ( 4 )应用格心格式的有限体积法对翼身组合体绕流进行了euler方程的数值模拟,同时引入各种加速收敛措施,与实验相比,得到了较为满意的计算结果。
The present thesis solves euler equations with quick parallel computing methods on grids . based on schwarz parallel algorithms , collectivity flow field numerical value solver can be gained via evaluating interface boundary cells by passing information 本文的主要目的是并行快速求解欧拉方程数值解,是以schwarz并行算法为理论依据,通过信息传递对内边界单元赋值,以得到总体流场的数值解。
Attempting to use conservative scheme to compute multi - component fluid via the extended euler equations gives rise to strong oscillations near material interface . such difficulty also occurs in common conservative scheme in lagrangian coordinate 守恒型格式在计算多介质问题的扩展euler方程组时在物质交界面附近会产生强烈的震荡,同样的困难存在于lagrange坐标系下一般的守恒型格式对多介质问题的计算中。
At last , a better idea is presented : in fact , the problem of computing the shape distance between two open curves can be changed to the problem of a functional extremum , therefore , we can get the shape distance through solving an euler equation 本文在最后还证明了这样一个结论,两条平面开曲线的形状距离的计算问题可以转化为一个泛函的极值问题,于是通过解一个欧拉方程就可以求出两条开曲线的形状距离。
Our researches in this paper give the solution to the problems above . and we successfully finish the aerodynamic optimization . the advances achieved in this paper are as follows : solving the euler equation with lu - sgs implicit algorithm on unstructured grids , mesh reordering will bring on imbalance 本文在研究过程中,对上述问题提出了相应的解决方法,并研制了相应的计算程序,使得结合模拟退火算法与正交分解的优化设计过程获得了成功。
4 . a 2 - d and 3 - d euler equations and n - s equations are solved using the cell - centered finite volume method and four - step runge - kutta scheme on the cartesian grids with standard convergence acceleration techniques such as local time stepping , enthalpy and implicit residual smoothing 使用jameson中心有限体积法和runge - kutta时间推进方法,求解了关于二维、三维复杂流场的euler 、 navier - stokes方程,采用了当地时间步长、隐式残值光顺等多种加速收敛方法。