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stagnation line
相关语句
  驻点线
    In this paper, the nonequilibrium viscous shock layer equations have been used to calculate the hypersonic flows over blunt bodies in the fore-body region ( including stagnation line and sonic line).
    本文从化学非平衡粘性激波层控制方程出发,用数值法计算了高超音速钝体绕流头部区流场(包括驻点线和音速线)。
短句来源
  “stagnation line”译为未确定词的双语例句
    NUMERICAL METHOD OF VISCOUS SHOCK-LAYER NEAR THE STAGNATION LINE OF A BLUNT BODY
    钝体驻点线附近粘性激波层的数值方法
短句来源
    The Stagnation Line Solution of the Equilibrium Flow with Radiation and Mass Injection
    考虑辐射的化学平衡流驻点线解
短句来源
    Before this only the firstorder scheme and loosely coupledmethod was successfully used in this research field. The gais model for chemically relaxingair consists of seven species(O,O_2,NO,N,NO ̄(+),N_2,e ̄(-))and seven substantial reactionsare considered. The calculated results are compared with existing numerical solutions solvedby first-order scheme in the literature along the stagnation line of the hemisphere,improvedresuIts are obatined.
    化学松弛气体考虑了七组元(O,O_2,NO,N,NO ̄(+),N_2,e ̄(-))和主要的七反应,在驻点线上的计算结果与前人结果比较表明,本文有较大改进。
短句来源
    The steady state simulations were performed on a one meter nose radius sphere at an altitude of 65 km and at free stream velocity of 8km/s , and the distribution of the temperature and mass fraction of species along the stagnation line , the wall temperature and heat transfer rate were obtained at two attack angles of flight ( α =0° and α =5°),and the data at an attack angle of zero were compared well with references.
    对再入高度为 6 5km和速度为 8km/s的再入体头部区域烧蚀流场进行了数值模拟 ,用飞行迎角α =0°的计算结果与国外文献进行了比较 ,符合得较好。 同时给出了三维小迎角α =5°的计算结果
短句来源
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  stagnation line
Numerical solutions of flow and heat transfer process on the unsteady flow of a compressible viscous fluid with variable gas properties in the vicinity of the stagnation line of an infinite swept cylinder are presented.
      
Unsteady compressible boundary layer flow on the stagnation line of an infinite swept cylinder
      
Investigation of swirling flow of a viscous gas near the stagnation line of a blunt body
      
Profiles of the rotational temperature along the stagnation line in the case of transverse flow over a cylinder are obtained.
      
Investigation of the system of equations for a compressible laminar boundary layer in the neighborhood of a stagnation line
      
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In this paper, the nonequilibrium viscous shock layer equations have been used to calculate the hypersonic flows over blunt bodies in the fore-body region ( including stagnation line and sonic line). Seven species (N2, O2, N, O, NO, NO + , e-) as well as seven chemical reaction equations of ionized air are considered. It is assumed that the chemical reactions proceed at finite rate, a binary diffusion model is used for nonequilibrium diffusion. Different boundary conditions are computed, including...

In this paper, the nonequilibrium viscous shock layer equations have been used to calculate the hypersonic flows over blunt bodies in the fore-body region ( including stagnation line and sonic line). Seven species (N2, O2, N, O, NO, NO + , e-) as well as seven chemical reaction equations of ionized air are considered. It is assumed that the chemical reactions proceed at finite rate, a binary diffusion model is used for nonequilibrium diffusion. Different boundary conditions are computed, including shock slip, wall slip, fully catalytic and noncatalytic wall conditions. The parameters of flowfield and electron density distributions are obtained and compared with relevant references.

本文从化学非平衡粘性激波层控制方程出发,用数值法计算了高超音速钝体绕流头部区流场(包括驻点线和音速线)。考虑了电离空气的七种主要成份(N_2,O_2,N,O,NO,NO~+,e~-)以及相互之间的七个化学反应方程式。认为化学反应的速率是有限的,非平衡扩散采用双组元扩散模型。对激波滑移、壁面滑移、完全催化壁和非催化壁等不同的边界条件进行了计算,得到了流场参数和电子密度分布情况,并与有关文献进行了比较。

The chemical equilibrium viscous shock-layer equations at stagnation line are solved numerically in this paper. The effects of radiation and mass injection are considered. The detailed line and continuum radiation models are included. The flowfield is devided into two zone as the surface mass injected, one is from the surface to v= 0 in which contains the injected species, and the other is from v= 0 to the shock in which there are no injected species.The minimum free energy method is used in determining...

The chemical equilibrium viscous shock-layer equations at stagnation line are solved numerically in this paper. The effects of radiation and mass injection are considered. The detailed line and continuum radiation models are included. The flowfield is devided into two zone as the surface mass injected, one is from the surface to v= 0 in which contains the injected species, and the other is from v= 0 to the shock in which there are no injected species.The minimum free energy method is used in determining the species concentrations. The effects of different injection rates, nose radius and free stream velocities on the convective and radiative heat transfer are discussed. The results are compared with those from references and they agree quite well with each other.

本文用数值方法求解了化学平衡的高超声速粘性激波层驻点线流场。考虑了辐射和质量引射对流场的影响。辐射模型采用线和连续谱模型。文中讨论了引射率、头部半径、来流速度对壁面传热的影响。与有关文献结果比较表明,本文的方法是可行的。

An explicit second-order upwind TVD scheme by H.C.Yee is first suc-cessfully extended to solve the viscous,diffussive,nonequilibrium,ionizing,hypersonic flowfields over a hemi-sphere.The governing gas-dynamic and species-continuity equations forlaminar flow are presented.The gas-dynamics/species continuity equations fully couplingprocedure is described in detail.Before this only the firstorder scheme and loosely coupledmethod was successfully used in this research field.The gais model for chemically relaxingair...

An explicit second-order upwind TVD scheme by H.C.Yee is first suc-cessfully extended to solve the viscous,diffussive,nonequilibrium,ionizing,hypersonic flowfields over a hemi-sphere.The governing gas-dynamic and species-continuity equations forlaminar flow are presented.The gas-dynamics/species continuity equations fully couplingprocedure is described in detail.Before this only the firstorder scheme and loosely coupledmethod was successfully used in this research field.The gais model for chemically relaxingair consists of seven species(O,O_2,NO,N,NO ̄(+),N_2,e ̄(-))and seven substantial reactionsare considered.The calculated results are compared with existing numerical solutions solvedby first-order scheme in the literature along the stagnation line of the hemisphere,improvedresuIts are obatined.

将H.C.Yee所发展的一种二阶迎风TVD格式运用于半球的高超声速化学非平衡黏性绕流的数值计算,详细介绍了流体力学方程组和化学组元守恒方程组全耦合求解的过程,以前这一研究领域中仅仅运用一阶格式及松散耦合的方法。化学松弛气体考虑了七组元(O,O_2,NO,N,NO ̄(+),N_2,e ̄(-))和主要的七反应,在驻点线上的计算结果与前人结果比较表明,本文有较大改进。

 
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