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无粘
相关语句
  inviscid
    NUMERICAL ANALYSIS OF INVISCID EQUILIBRIUM AND NON-EQUILIBRIUM HYPERSONIC FLOW PAST SMALL BLUNT-NOSED CONES
    小钝头锥无粘平衡、非平衡绕流流场的数值分析
短句来源
    NUMERICAL PRACTICE FOR CALCULATING INVISCID FLOW FIELD USING MACCORMACK TWO-STEP SCHEME
    用MacCormack二步格式计算无粘流场的数值实践
短句来源
    NUMERICAL CALCULATIONS OF INVISCID TRANSONIC FLOWS OVER WINGS
    机翼无粘跨音速绕流数值计算
短句来源
    The Numerical Simulation of Transonic Inviscid Flow over Oscillating Airfoils
    跨声速无粘流绕振动翼型流动的数值模拟
短句来源
    Numerical Simulation of Hypersonic Inviscid Flow Around the HERMES Configuration
    绕HERMES外形高超声速无粘流动的数值模拟
短句来源
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  non viscous
    THE PURE BOUNDARY INTEGRAL FORMULATION FOR NONLINEAR EQUATION OF STEADY COMPRESSIBLE NONVISCOUS FLOW
    定常可压缩无粘流非线性方程解的完全边界积分表示式
短句来源
    A pure boundary integral formulation for the nonlinear equation of steady compressible nonviscous flow is given by using p Vas the dependent variable and thus the computational dimension of the problem is reduced by one.
    本文以ρV为因变量将可压缩等熵无粘流非线性方程的解表示成完全边界积分形式,从而将问题的计算维数降低一维。
短句来源
    The AUMS scheme in the form of arbitrary curvilinear coordinates is given first and then is put in conjunction with the MUSCL scheme which has third order accuracy. And then, using the implicit time marching method LU SGS, the numerical simulation of non viscous transonic and supersonic flows within the cascade with typical double circular arc blades. The calculation results presented in this paper show that they coincide well with the results published in the literature.
    给出了AUSM 格式在任意曲线坐标下的形式,将AUSM 格式和三阶精度MUSCL格式融合,并结合LU-SGS隐式时间推进法,对典型双圆弧叶栅无粘跨音速和超音速流动进行了数值模拟.本文计算结果与文献计算结果相符
短句来源
    The two dimensional Reynolds averaged N-S equations were resolved on unstructured grids using finite volume method, the Vanleer fluxes vector splitting scheme was used for the non viscous terms, and the two layers Baldwin Lomax algebraic turbulent model was used for turbulent viscosity.
    N -S方程的无粘项采用有限体积法在非结构网格上进行空间离散 ,通量分裂采用二阶精度的Vanleer格式 ,紊流粘性系数采用Bald win -Lomax二层代数紊流模型计算。
短句来源
  “无粘”译为未确定词的双语例句
    IRVISCOUS-VISCOUS FRACTIONAL METHOD TO SOLVE N-S EQUATIAN SET FOR COMPRESSIBLE FLUID
    求解可压缩N-S方程的无粘-粘性分数步法
短句来源
    Two important components of turbine long blade aerodynamic design system- S2 design calculation and S1 flow solution is concentrated on.
    围绕蒸汽涡轮长叶片级气动设计体系中的两个重要的环节——涡轮级S2流面反问题设计计算和任意旋成流面上的二维叶栅网格生成方法及无粘流场数值计算方法开展了部分工作。
短句来源
    Based on the unstructured grids generated with the above function, and in combination with finite volume method, hypersonic nonequilibrium flows with chemical reactions were successfully calculated.
    基于生成的网格采用有限体积法研究无粘高超音速化学非平衡流的流场分布 ,生成的网格能够成功的运用于高超音速化学非平衡流的数值计算
短句来源
    An implicit finite volume upwind space-marching CFD solver,i. e. Single-Sweep Parabolized Navier-Stokes Algorithm(SSPNS),is developed by integrating the PNS equations with LU-SGS method in the streamwise direction.
    在有限体积法框架下,采用空间推进算法SSPNS(Single-Sweep Parabolized Navier-Stokes Algorithm)求解抛物化NS方程(即PNS方程),在流向采用LU-SGS隐式积分,而横向无粘和粘性通量则分别采用AUSM系列格式和中心格式计算。
短句来源
    NUMERICAL SOLUTION FOR THE SUPERSONIC INVISCID FLOW ABOUT NON-SYMMETRICAL BODIES
    非对称体超音速无粘绕流流场数值计算
短句来源
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  inviscid
In [1, 2] Gonor considered the problem of imperfect inviscid gas flow about conical bodies at high supersonic speeds.
      
In the present paper we consider the problem of the stability of radial motion of the spherical boundary of a gas bubble in an incompressible inviscid liquid under the action of variable external pressure.
      
Inviscid flow past a ducted axisymmetric body with annular elliptical region
      
The articles [1-3] are devoted to the calculation of the radiant field and the temperature field for a given flow of a perfect inviscid nonheat-conducting radiating gas with constant absorption coefficient.
      
We consider the problem of steady flow of an inviscid, non-heat-conducting gas about a delta wing which is spherically blunted at the nose and cylindrlcally blunded on the leading edges, at an angle of attack.
      
更多          
  non viscous
Spreading of viscous droplets on a non viscous liquid
      
For this reason we propose an alternative solution, in which the topographic surface is modified in such a way that flooding it with a non viscous fluid will produce the same lakes as flooding the original relief with a viscous fluid.
      
These models are the non viscous fluid, the Newtonian viscous fluid, and the elastic hookean solid.
      


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 method to calculate nonlinear compressibility effects of airfoils in subsonic flow based on the method of finite elementary solution (MFES) is presented. Using the progressive iterative, the method allows direct extension of MFES to nonlinear inviscid compressible flow. Thus it provides a new approach to the solution of the nonlinear equations.A computer program was completed in FORTRAN IV. The comparison of the results obtained with those of exact and other theoretical solutions shows superiority of this...

A method to calculate nonlinear compressibility effects of airfoils in subsonic flow based on the method of finite elementary solution (MFES) is presented. Using the progressive iterative, the method allows direct extension of MFES to nonlinear inviscid compressible flow. Thus it provides a new approach to the solution of the nonlinear equations.A computer program was completed in FORTRAN IV. The comparison of the results obtained with those of exact and other theoretical solutions shows superiority of this method to the ordinary method of finite difference, especially in the airfoil nose region.

本文从有限基本解方法出发,介绍一种计算亚音速流中非线性压缩性效应的方法。采用逐步逼近的办法,可以把有限基本解方法推广到求解非线性的无粘可压流体,从而为非线性方程的求解提供了新的途径。 编制了FORTRAN语言程序。与精确解和其他理论值的比较表明,结果比传统的有限差分法好,尤其是在翼型头部。

The paper describes a numerical method for evaluation of the three-dimensional inviscid supersonic flow about the re-entry vehicles of non-symmetrical bodies. The method is devoted to determining the initial-boundary value problem for hyperbolic partial differential equations in the conservation law form. The MacCormack' s explicit finite-difference schemes with second order accuracy is adopted. For a bent sphere-cones, different oriented cylindrical coordinate systems are used in different cone regions. The...

The paper describes a numerical method for evaluation of the three-dimensional inviscid supersonic flow about the re-entry vehicles of non-symmetrical bodies. The method is devoted to determining the initial-boundary value problem for hyperbolic partial differential equations in the conservation law form. The MacCormack' s explicit finite-difference schemes with second order accuracy is adopted. For a bent sphere-cones, different oriented cylindrical coordinate systems are used in different cone regions. The computation of the body surface points is different from reference[ 1,2].The numerical examples of the bent sphere-cones and the re-entry vechicles with control flaps have been worked out to demonstrate the capability of this technique. The accuracy of the results has been examined.

本文给出了非对称再入飞行器的超音速三维无粘流场的数值计算方法。它归结为求解三个自变量—阶定常拟线性双曲型偏微分方程组的初边值问题。采用MacCormack二步显式差分格式。 为了说明计算方法的实际能力,对弯头钝锥和带控制翼的再入体作了计算。其精确度是令人满意的。

 
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