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   采用有限 在 航空航天科学与工程 分类中 的翻译结果: 查询用时:0.742秒
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采用有限
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  a finite
    A 3d LU-SGS computational code is developed to solve the hypersonic flows, which is modeled by the compressible Reynold averaged three-dimension Navier-Stokes equations and with a use of a finite volume formulation, the convective parts are discretized with the Harten TVD scheme, turbulent effects are modeled utilizing Menter SST tow equation turbulence model.
    本文数值方法基于Reynold平均的Navier-Stokes方程,采用有限体积法离散计算区域,对流项使用Harten TVD格式进行流场求解,湍流部分应用Menter SST两方程湍流模型,建立了隐式LU-SGS方法的求解三维计算程序,用来模拟高超声速流场。
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    In order to simulate the flow field around parachute during terminal descent, a finite volume method and Spalart-Allmaras turbulent model are used to solve N-S equations.
    文中采用有限体积法求解不可压流的N -S方程 ,采用Spalart-Allmaras(SA)模型作为湍流模型 ,以模拟降落伞稳定下降阶段时的流场特性。
短句来源
    By using a finite volume method to solve the Navier-Stokes equations, two-dimensional vibrating cascade flow was computed.
    采用有限体(面)积法求解Navier-Stokes方程,完成了二维振动叶栅流动数值模拟。
短句来源
    Transonic flow over an oscillating airfoil has been computed by solving the Euler equations. A finite volume scheme is used to spatially discretize the integral form of the Euler equations for a moving domain, and a symmetric TVD scheme is presented to construct dissipative terms.
    从积分形式的非定常Euler方程出发,在固联于振动冀型的贴体坐标系下,采用有限体积法进行离散,并根据对称型TVD格式构造相应的数值通量,数值模拟了振动翼型的非定常跨音速绕流的变化过程。
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    The approach is to solve the Euler equations in a rotor fixed frame of reference using a finite volume method.
    采用有限体积法在桨叶固接坐标系直接求解三维欧拉方程。
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  “采用有限”译为未确定词的双语例句
    First, the repeated structural analyses for static and dynamic characteristics are needed in the integrated optimization of composite wing structures.
    首先,复合材料翼面结构综合优化设计需要反复进行结构静力和动力特性分析,如果采用有限元模型(Finite Element Model,简称FEM),则其工作量太大。
短句来源
    (2) Issues of the nonlinear flutter of the 3-D wing which stiffness is the hard spring and freeplay nonlinear are studied by using the mothod of finite element and the theories of the qusi-steady aerodynamics and the Hopf bifurcation.
    (2) 采用有限元法、准定常气动理论和分叉理论,研究了带操纵面硬弹簧和间隙非线性的三元机翼非线性颤振问题。 建立了带操纵面硬弹簧和间隙非线性的三元机翼非线性颤振模型;
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    FGA-FEM was put forward to optimize the floatwall structure, and FGA-FEM combined Fuzzy Genetic Algorithm (FGA) and Finite Element Method (FEM).
    本文提出一种采用有限元方法(FEM)和模糊遗传算法相结合的方法即模糊遗传算法-有限元的结构优化方法(FGA-FEM),并将该方法应用于燃烧室浮动壁结构的优化计算和分析,取得了较好的效果。
短句来源
    This paper used the finite element method to compute the temperature field, and combined finite element with analytic solution to develop a calculation of thermal stresses.
    本文采用有限元数值分析方法计算多层圆管的温度场,并把解析解与有限元相结合,提出一种求解其热应力的计算方法.
短句来源
    Through static, modal and crack stress intensity factor analysis, the vibration stress of blade under rotating state before fracture can b e calculated out finally.
    然后采用有限元数值计算方法对叶片进行静力分析、模态分析及裂纹应力强度因子计算 ,最后反推出叶片在旋转状态下振动应力值的大小。
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  a finite
In all these cases we actually show that Γ=π1(M) has a finite index subgroup which is mapped onto a nonabelian free group.
      
Using these monomial bases we prove that the image of the transfer for a general linear group over a finite field is a principal ideal in the ring of invariants.
      
We prove the following result: LetG be a finite irreducible linear group.
      
The first one is a conjecture of Ian Hughes which states that iff1, ..., fn are primary invariants of a finite linear groupG, then the least common multiple of the degrees of thefi is a multiple of the exponent ofG.
      
More precisely, each orbit of the above action intersects one componentX ofQ in a finite number of points and the action of PGL4 restricted on each componentX is equivalent to the action of a finite groupGX onX which can be explicitely computed.
      
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A general program using finite-difference method is written to calculate the flow field of supersonic axisymmetric nose inlet. This program is suitable to the direct problem of aerodynamic design of inlets e. g. pitot-type, single-cone, bicone, triple-cone and isentropic cone etc. Since "seperation singularity" difference method and implicit-explicit difference scheme are adopted in the calculation of inviscid flow field in the inlet, results of calculation are obtained with second order accuracy at boundary...

A general program using finite-difference method is written to calculate the flow field of supersonic axisymmetric nose inlet. This program is suitable to the direct problem of aerodynamic design of inlets e. g. pitot-type, single-cone, bicone, triple-cone and isentropic cone etc. Since "seperation singularity" difference method and implicit-explicit difference scheme are adopted in the calculation of inviscid flow field in the inlet, results of calculation are obtained with second order accuracy at boundary points and internal points, as well as near singular points. This program can offer required internal and external flow characteristics of inlets.Numerical results for five examples are in satisfactory agreement with corresponding results obtained from the method of characteristics and experimental data.

为了计算超音速轴对称头部进气道的流场,采用有限差分法编制了一个通用计算程序。该程序适用于皮托式、单锥、双锥、三锥、等熵锥等各种进气道的正问题气动设计。由于在进气道无粘流场计算中,采用了分离奇性的差分方法及混合使用显、隐差分格式,所以在边界点和内点及奇点邻域,计算结果均达到二级精度。程序可瑜出所需要的进气道各内流特性及外流特性。 文中列生了五个计算实例,并与特征线法计算结果和实验结果作了比较。符合程度令人满意。

A general formulation for oscillatory subsonic potential flows around three-dimensional bodies of various configuration and its application to the calculation of dynamic stability derivatives of the aircraft are presented. By applying the Green function method, we obtained an integro-differential equation relating the perturbation velocity potential to its normal derivatives on the surface of the body. In order to solve this equation, the surface of the body and its wave are divided into small quadrilateral...

A general formulation for oscillatory subsonic potential flows around three-dimensional bodies of various configuration and its application to the calculation of dynamic stability derivatives of the aircraft are presented. By applying the Green function method, we obtained an integro-differential equation relating the perturbation velocity potential to its normal derivatives on the surface of the body. In order to solve this equation, the surface of the body and its wave are divided into small quadrilateral elements. The unknown φ and its derivatives are assumed to be constant within each element. Thus the integro-differential equation reduces to a set of differential-delay equations in time. This set of equations can be used as the basis of a general method for the fully unsteady flow calculation. For oscillatory subsonic potential flow, this set of equations further reduces to a set of linear algebraic equations which is solved numerically to yield the values of φ; at the centroid of each element. The pressure coefficient is evaluated by the finite difference method. The lift and the moment coefficients are determined by numerical integration of the pressure coefficient. The dynamic stability derivatives are obtained from the imaginary parts of the lift and the moment coefficients.The formulations in this paper are embedded into a general computer program. Several typical numerical results have been obtained by means of this program. Figure 2 shows the distribution of lift coefficient CL along the middle section for a rectangular wing oscillating in pitch with λ =2, τ =0.001, M∞ = 0, K = 2 .The result is identical to the original calculation by Merino. Figure 3 shows the distribution of pressure coefficient Cp for a harmonically oscillating spheroid witha/b= 8, M∞=0.5, K=2 . The result is in good agreement with the analytical solution of wave equation.Figures 5 , 6, 7 show the distributions of lift coefficient CL at various stations of an aircraft (wing-body-tail combination) oscillating in pitch with M∞ = 0.6, K -0.005, 0.01. Vable 2 shows the dynamic stability derivatives CLa, Cma of the aircraft. The. results are in good agreement with the experimental data.

本文介绍处理不同外形三维物体亚音速振荡绕流一种统一的方法。本方法的主要特点是采用有限元素法直接解由格林定理导出的物面速势积分-微分方程以求得物面的速势分布,然后再用有限差分法对速势进行微分求物面的压力分布。 由于本方法理论上比较严格,适用于复杂外形物体绕流的计算,所得结果又比较准确,因此近几年来在国外得到越来越广泛的应用。在本文中,采用了与有关文献相同的基本方程,但在气动影响系数的计算上略有不同,本文并将这一方法应用于飞行器动导数的计算,所得的结果与实验结果符合。

In order to calculate the lifts of rectangular wings with different winglets at subsonic speeds, we have adopted the finite element method which divides spanwise lattice and determines spanwise locations of control points by means of a constant roll-angle method. The induced drags are also calculated by using combined flow field method.As the results of calculating various configuration of a winglet, we have found out some rules affecting the lift and drag characteristics of wings with winglets and picked out...

In order to calculate the lifts of rectangular wings with different winglets at subsonic speeds, we have adopted the finite element method which divides spanwise lattice and determines spanwise locations of control points by means of a constant roll-angle method. The induced drags are also calculated by using combined flow field method.As the results of calculating various configuration of a winglet, we have found out some rules affecting the lift and drag characteristics of wings with winglets and picked out a favourable configuration from them. The aerodynamic mechanism of winglets is also discussed.

本文采用的有限基本解方法,以等转角法划分展向网格和确定展向控制点位置。对带翼梢小翼亚音速矩形翼进行了升力计尊,并用联合流场法计算了诱导阻力。从各种方案的翼梢小翼计算中,找到了一些影响机翼升阻特性的规律和较佳方案,并对其机理作了分析。

 
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