A numerical Calculating method of inviscid steady transonic flow over wings is presented.
本文介绍机翼跨音速定常无粘绕流的一种数值计算方法。
This characteristic is some summary to a certain number of results obtained in transonic flow study.
这一特征对跨声速流动中的若干结果有一定概括性。
And optimization computation for reducing drag of Shockwave of single airfoil in transonic flow is also successful.
同时进行了单段翼型跨音速降低激波阻力的优化设计。
Using the improved method we studied inviscid and viscous transonic flow in turbomachinery based on Euler and Navier Stokes equations.
计算结果表明，本方法是透平机械内部跨音速流动计算的强有力的手段。
The new method is used to study transonic flow in cascades and one kind of complex unsteady transonic axisymmetric flow in arc breaker.
利用本文的方法，分别计算了跨声速叶栅流动和工程中一类复杂非定常轴对称跨声速流动。
A kernel function method and the results of computing unsteady load on three-dimensional wings in transonic flow are presented in this paper.
本文给出了在跨音速流动中，计算三维机翼非定常载荷分布的核函数法和计算结果。
And the two-dimensional shock-wave relations of the stream-line coordinates are also derived as the shock wave may be exist in transonic flow field.
由于在跨音速流场内可能存在激波，所以也导出了流线座标系二维激波关系式。
The transonic flow field around NACA 0012 airfoil is calculated by finite element method from pressure minimum integration, full potential equation being used.
本文采用压强极小积分有限元法计算了NACA 0012翼型的跨音速流场。出发方程为全速位方程。
The mutiple-solution phenomenon of steady transonic flow about two-dimensional plane cascade using the Time-Marching method for the Euler equations is examined.
本文用时间推进法求解欧拉方程组计算二维平面叶栅绕流问题数值实验是否有多重解现象。
An implicit flux vector splitting form in one-step with second-order accuracy was proposed for solving the transonic flow fields of air channels and cascades of diffusers.
提出了二阶精度隐式矢通量单步差分格式并用来求解跨压器进气道、叶栅的跨音流场。
An inviscid-viscous interaction method based on the inviscid time marching computer code has been employed to calculate the transonic flow field of two dimensional cascade.
二维跨音速叶栅流场的计算是在无粘时间相关法计算程序的基础上采用无粘-边界层迭代而得。
The aerodynamic undamping phenomena and the relevant mechanism are investigated for the aerospace launch vehicle undergoing fluid-structure coupling oscillation in transonic flow.
研究跨音速飞行航天器的流-固耦合振动非阻尼现象的作用机理。
According to the "General Theory of Three-Dimensional flow in Turbomachines", the quasi-three dimensional calculation of the transonic flow field has been achieved for a compressor rotor.
本文依据三元流动的通用理论，完成了一个跨声速压气机转子流场的准三元迭代计算。
The transonic flow computation is performed by the use of conservative full-potential equation with exact boundary conditions and the efficient iteration scheme in finite difference method AF2.
跨音速计算采用守恒型金位势方程，精确边界条件和AF 2高效有限差分迭代算法。
In this paper, the adaptive parallel Multigrid algorithm is applied in solving transonic flow equation with large disturbance in the axial direction and small disturbance in the transverse direction.
本文运用自适应并行多重网格法求解了轴向大扰动、径向小扰动的跨音速方程。
An improved streamline curvature numerical method is modified and applied to better approximate the flow fields of multi-stage transonic axial compressors.
本文采用改进的流线曲率法对跨声速多级轴流压气机非设计点进行了性能模拟。
The present paper computed the viscous flow of S_1 flow surfaces in some transonic turbine vane cascade by using the computational software FLUENT.
使用FLUENT软件对某型跨音速涡轮叶栅的导叶进行了S_1流面的粘性流动计算。
A numerical method is presented for predicting unsteady transonic aerodynamic flow about aircraft wings with control surface.
本文介绍一种带操纵面机翼的非定常跨声速流的有限差分计算方法。
The paper presents some research works on the internal flow shock wave measurement of transonic compressor by PIV technique.
在跨音压气机试验台上进行了用PIV技术测量内流激波结构的试验研究。
Numerical calculations were performed on a two-stage transonic fan and a five-stage compressor. The two-stage fan flow predictions show a good agreement with experimental data.
对某双级跨音速风扇及五级压气机流场进行了计算，双级风扇各状态的计算结果与实验数据吻合较好。
Numerical analyses of the transonic nozzle inviscid flow and supersonic jet impingement on a jet TAB are presented.
采用数值分析方法分析了跨声速喷管无粘流动和超声速射流对挡流板的冲击流场。
The effect of acoustic excitation on the flow asymmetry over a slender body in compressible flows was investigated in a transonic wind tunnel.
在跨声速风洞中研究了声激励对于可压缩流中细长旋成体大迎角流动非对称性的影响效果。
The transonic turbulent flow around a blunt nosed and short body at large angle of attack was calculated and analysed by using numerical simulation method to solve the full N S equations.
采用数值模拟求解NS方程方法计算与分析了绕大钝头短体外形的跨音速大迎角时的湍流流动。
In the calculation of flow field in 2-d transonic cascade, wave has been exactly captured and results are satisfactory.
在平面叶栅跨音流场的计算中，较好地捕获了激波，与实验比较，结果令人满意。
An improved streamline curvature numerical method is modified and applied to better approximate the flow fields of multi-stage transonic axial compressors.
本文采用改进的流线曲率法+对跨声速多级轴流压气机非设计点进行了性能模拟。
This paper represents a CFD method for the design of NLF airfoils directly under transonic viscous flow conditions.
本文介绍一种设计跨声速自然层流翼型的计算流体力学（CFD）方法。
The paper describes experimental flow study results of trailing edges of transonic turbine blades in a closed transonic wind tunnel with discussing its mechanism.
本文叙述了在跨音速风洞中模拟跨音速透平叶片尾缘流动的试验结果。分析了跨音速透平叶片尾缘流动的机理。
The experimental investigation on aeroelastic instability and dynamic response of the BF-1 rotors by a transonic axial-flow compressor test rig are presented in this paper.
本文介绍了在跨音压气机试验台上对BF - 1系列转子开展气动弹性失稳和动态响应的实验研究工作。
As an application example, the 2-d inviscid transonic cascade flow is solved by using adaptive grids.
作为应用实例，本文将自适应网格用于二维无粘跨音速叶栅流场计算。
A 3d numerical simulation software was developed to calculate the tip-clearance flow of ATS-2, a high-loading transonic compressor, and the results were compared with the experiments.
利用自行开发的叶轮机三维数值模拟软件对高负荷跨音压气机ats - 2转子进行了带叶尖间隙的三维流动数值模拟，并与实验的结果进行了比较。
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