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跨声速绕流计算
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  “跨声速绕流计算”译为未确定词的双语例句
     A NEW METHOD FOR CALCULATING THE PLANE TRANSONIC FLOW PAST CASCADE
     平面叶栅跨声速绕流计算的一种新方法
短句来源
     CALCULATION OF TRANSONIC FLOW PASSING CASCADE OF ARBITRARY AIRFOILS ON GENERAL SURFACE OF REVOLUTION
     任意旋成面叶栅的跨声速绕流计算
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  相似匹配句对
     Transonic Flow Simulation for Wing-Body Configurations
     机翼机身跨声速绕流计算
短句来源
     Computation of Transonic Viscous Flow of a Projectile
     弹丸跨声速粘性绕流数值计算
短句来源
     CALCULATION OF TRANSONIC FLOW PASSING CASCADE OF ARBITRARY AIRFOILS ON GENERAL SURFACE OF REVOLUTION
     任意旋成面叶栅的跨声速绕流计算
短句来源
     A NEW METHOD FOR CALCULATING THE PLANE TRANSONIC FLOW PAST CASCADE
     平面叶栅跨声速绕流计算的一种新方法
短句来源
     THE NUMERICAL CALCULATION OF THE SUPERSONIC FLOW AROUND COMBINED BODIES
     组合体超声速绕流计算
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The present method can be regarded as a combination of the time marching finite volume method and the streamline iteration method. It is used for the calculation of the transonic flow passing cascade of arbitrary airfoils on general surface of revolution. On a stream surface of revolution the grid used in this method is formed by a set of streamlines which are unknown in advance and have to be iterated successively in the process of computation and a set of fixed pitchwise lines. The use of streamlines as gridlines...

The present method can be regarded as a combination of the time marching finite volume method and the streamline iteration method. It is used for the calculation of the transonic flow passing cascade of arbitrary airfoils on general surface of revolution. On a stream surface of revolution the grid used in this method is formed by a set of streamlines which are unknown in advance and have to be iterated successively in the process of computation and a set of fixed pitchwise lines. The use of streamlines as gridlines makes the distribetions of gridlines more reasonable and greatly simplifies the finite difference scheme. In this paper the successive mesh refinement technique is used in order to speed up convergence of the process of computation.

本文中的方法是把时间推进有限体积法和流线迭代法结合起来,用以解决任意旋成面叶栅跨声速绕流的计算问题。在旋成流面上,网格是由一族流线及一族固定的节距线所组成的。流线的位置预先并不知道,在计算过程中需要逐步加以修正。采用流线作为一族网格线可使网格线的分布更为合理,并使差分格式简化。同时,为了加速计算过程的收敛,在本计算中采用逐步加密网格技术。

A field integral method has been applied to calculate model support interferences for transonic flows over models with embedded supersonic regions. The program based on the integral formulation of transonic full potential equation is presented to calculate the aerodynamic coefficients of the model with and without a horizontal sting (rear sting), and the difference between the aerodynamic coefficients of the two conditions is used to correct the support interference. In this paper, the distribution of the singularities...

A field integral method has been applied to calculate model support interferences for transonic flows over models with embedded supersonic regions. The program based on the integral formulation of transonic full potential equation is presented to calculate the aerodynamic coefficients of the model with and without a horizontal sting (rear sting), and the difference between the aerodynamic coefficients of the two conditions is used to correct the support interference. In this paper, the distribution of the singularities of source and vorticity is based on panel method, and the field grid is divided by the means of penetrating grid, in which the body configuration is ignored and the intensity of the field sources in body is zero. The calculations have been carried out for two models: the model of double vertical tails on body and GBM-03 model. The results of the present method are compared to those given by earlier experimental data.

提出了一种计算高速风洞支架系统对飞行器模型纵向气动力干扰量的数值计算方法 ,从跨声速全位势积分方程出发 ,编制了适用于飞行器全机模型及其带支架情况下的跨声速绕流计算程序。通过对双垂尾模型和GBM 0 3模型两个算例的计算 ,讨论了尾支撑位置及其几何外形参数对模型气动力的影响 ,并对GBM 0 3模型带短支杆情况下的纵向实验结果进行了修正。表明该方法对于分析研究风洞模型支架干扰问题并进行支架干扰修正是可行的、有效的 ,可以作为选择尾支撑位置及其几何外形参数和对跨声速风洞纵向实验结果进行支架干扰修正的工具。

 
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