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龙格
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  runge
    COMPUTATION OF COMPRESSIBLE FLOW USING RUNGE KUTTA TIME STEPPING
    可压流的龙格-库塔时间步进求解法及其应用
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    This paper presents the critical frequency prewarping approximation to analyze the frequency character of the system model with wide frequency band, and compares the method with bilinear approximation and fourth order Runge Kutta method.
    以频带较宽的典型环节为例, 对系统频率特性进行了分析, 同时, 将其与双线性变换及四阶龙格-库塔法的计算结果进行了比较。
短句来源
    Different from the numerical simulation used by Rai , Takahashi and Dorney , we employed Euler equation and Jameson's four stage Runge Kutta scheme to study the unsteady flow in turbine stage with inlet temperature distortion.
    采用 Jameson的四阶龙格 -库塔法研究了高压涡轮叶栅进口有温度畸变时的涡轮流场。
短句来源
    By using finite volume approach for numerical approximation and Runge Kutta time stepping advance,Euler/Navier Stokes equations are solved.
    这两种格式的方法都采用有限体积法进行离散 ,并用龙格—库塔时间推进法求解。
短句来源
    The flow model of multiple constituents finite rate unsteady state chemical reaction was used in numerical simulation, and finite volume TVD scheme used in solving convection term of the equation group. The source term generated by chemical reaction was solved by four order Runge Kutta algorithm.
    数值模拟采用多组分含有限速率非平衡化学反应流动模型 ,利用有限体积TVD数值格式求解方程组的对流项 ,对于化学反应造成的源项则采用四阶龙格库塔求解。
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    The control surface motion equation was marched by Runge-Kutta method in time domain.
    通过与气动力方程的联立求解,在时域内用四步龙格-库塔方法求解结构运动方程。
短句来源
    Attitude algorithm of strapdown inertial navigation system using 4-order Runge-Kutta
    四阶龙格—库塔法在捷联惯导系统姿态解算中的应用
短句来源
    Based on the unstructured grid, Euler equations are solved using the cell-centered finite volume spatial discretization and four-stage Runge-Kutta time-stepping scheme with standard convergence acceleration techniques such as local time stepping and implicit residual smoothing.
    在对非结构网格生成方法研究的基础上,用格心格式的中心差分有限体积法,对飞机的当量旋成体流场进行空间离散,用四步龙格—库塔方法作显式时间推进,同时采用当地时间步长和隐式残值光顺的技术加速收敛。
短句来源
    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
    Here, we use the method of numerical analysis to solve the dynamic equations of aerocraft.
    在求解飞机运动方程的过程中,采用了龙格——库塔法等数值的方法。
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  runge
Its dynamic behaviors are investigated by numerical Runge-Kutta method.
      
Second, The Runge-Kutta arithmetic is used to calculate the dynamical parameters of the micro actuator; the SIMULINK module of MATLAB is used to build the dynamical simulating model and then simulate it.
      
The Runge-Kutta method is used to solve the ordinary differential equations of the model.
      
Some neutral curves for the limiting case of a narrow gap were obtained in [2] by the Runge-Kutta method together with the intersecting line method, and the case of small Reynolds numbers and arbitrary gaps was also considered.
      
The results are obtained by the finite-volume solution of the Euler equations using higher-order TVD Runge-Kutta schemes.
      
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A numerical method for calculating a fully-coupled model of one-dimensional two-phase nozzle flow is described in brief. Governing equations are derived. The Runge-Kutta-Gill method is adopted to solve the equations numerically. The solution for uniform acceleration of gas phase is utilized as an approximate solution for the dimensionless distance x*(=x/L) = 0 to 0.02,i.e.ug = ax*. The initial value of a is determined by a trial and error approach and then checked at the throat. The solution is continued to...

A numerical method for calculating a fully-coupled model of one-dimensional two-phase nozzle flow is described in brief. Governing equations are derived. The Runge-Kutta-Gill method is adopted to solve the equations numerically. The solution for uniform acceleration of gas phase is utilized as an approximate solution for the dimensionless distance x*(=x/L) = 0 to 0.02,i.e.ug = ax*. The initial value of a is determined by a trial and error approach and then checked at the throat. The solution is continued to the throat where the conditions must be satisfied. To eliminate the singularity of the equation, a superseding variable is introduced. The computations are performed for velocity-lag as well as temperature-lag of five parsticle sizes and two ratios of particle to gas flow rates.Temperature, pressure and velocity distributions of both gas and particle along the length of the nozzle are also obtained.In addition, various modes of one-dimensional two-phase nozzle flow have also been briefly reviewed.

本文对控制方程组作了无因次处理,用龙格-库塔-基尔法进行了数值解。计算了五种粒度及两种微粒-气体质量流率比下微粒速度滞后及温度滞后;气相和凝相参数沿喷管长度的变化。分析讨论了所获得的结果,并简要地评论了几种一维两相喷管流模型。

By means of bifurcation analysis and catastrophe theory methodology,this paper explores the effects of various kinds of control systems of an aircraft in rolling maneuver on occuring jump and limit cycle phenomena,enhancing critical roll rate,extending effective region of control surface,and improving time responses.These systems involve ordinary fedback control system,aileron-roudder-interconnect(ARI)system,stability-axis yaw damper and direct force control system.The results have been verified by those time...

By means of bifurcation analysis and catastrophe theory methodology,this paper explores the effects of various kinds of control systems of an aircraft in rolling maneuver on occuring jump and limit cycle phenomena,enhancing critical roll rate,extending effective region of control surface,and improving time responses.These systems involve ordinary fedback control system,aileron-roudder-interconnect(ARI)system,stability-axis yaw damper and direct force control system.The results have been verified by those time histories which were accomplished by a fourth o-der Runge-Kutta integration routine.

本文用分支和突变理论的方法,着重探讨急滚机动飞行时飞机上的各类控制系统,对突跃和极限环现象的发生,临时滚转速率的提高,舵面可操纵范围的扩大,以及时间响应的改善等方面的影响。这些系统包括:常规的自动器,ARI系统,稳定轴偏航阻尼器和直接力控制系统等。文中对所得结论用四阶龙格-库特积分程序求得的时间历程作了验证。

This paper deals with the heat transfer of trapezoidal fin under the condit- ion of radiation and convection. By applying 4th order Runge-Kutta integration scheme and Newton-Raphson iteration technique in numerical solution, the lengthwise temperature distribution of the fin is obtainedj the influences of various parameters, including thermal conductivity, emissivity, temperature at the base of the fin, length of the fin, and distance between neighbouring fins, on the fins' heat transfer are analyzed. Furthermore,...

This paper deals with the heat transfer of trapezoidal fin under the condit- ion of radiation and convection. By applying 4th order Runge-Kutta integration scheme and Newton-Raphson iteration technique in numerical solution, the lengthwise temperature distribution of the fin is obtainedj the influences of various parameters, including thermal conductivity, emissivity, temperature at the base of the fin, length of the fin, and distance between neighbouring fins, on the fins' heat transfer are analyzed. Furthermore, a comparison is made between the effects of heat transfer of different kinds of fins: the rectangular and triangular fins which taking radiation into accountl the trapezoidal fin which neglecting radiation These results are of important significance for engineering design.

本文研究了在辐射和对流条件下梯形肋片的传热,应用四阶龙格-库塔法和牛顿-拉伐森迭代法进行数值求解,得出肋片沿肋高方向的温度分布;进一步分析了导热系数、辐射率、肋根温度、肋高和肋间距等参数对肋片传热的影响。比较了考虑辐射矩形肋、三角形肋和不考虑幅射的梯形肋的传热情况。结果对工程设计具有重要意义。

 
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