Empirical results are needed in the transonic Mach regime.
在跨音速马赫数范围内需要经验结果。
In this paper some points concerning transonic potential method are briefly reviewed.
简要地回顾并讨论了传统位势方法之不足。
Numerical simulation of viscous flows through multistage transonic fans was carried out.
进行了多级跨音速风扇粘性流动的数值模拟研究。
An implicit time-marching method is presented for solving the transonic Euler equations.
本文提出了求解跨音速欧拉方程的一种隐式时间推进法。
An iteration method is used for computing the transonic pressure distribution on a flexible wing.
本文采用迭代求解的方法计算弹性机翼的跨音速压强分布。
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。
Flapping and rotary gap have been investigated with the help of transonic unsteady aerodynamic forces.
使用跨音速非定常空气动力，对扑动间隙和旋转间隙进行研究。
Coupled with the structural equations, the models for transonic aeroelasticity in state-space are got.
耦合结构动力学方程，建立了基于状态空间的跨声速气动弹性分析模型。
Several computed results of transonic turbine cascades are presented to illustrate the method's capabilities.
为论证方法的有效性，给出了几个跨音速涡轮叶栅的计算结果。
A finite difference method for computing the axisymmetric, transonic flows over nacelle is presented in this paper.
本文考虑轴对称跨音速进气道外流场的有限差分计算方法。
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。
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。
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。
This paper is a report of experimental pressure. Measurement research for NACA0012 airfoil in NH-1 transonic wind tunnel.
本文为NACA0012翼型在NH - 1风洞进行跨音速二维测压实验的研究报告。
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。
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。
This paper deals with the inverse design problem of transonic turbine cascade in the hodograph plane by the finite area method.
本文给出了基于有限面积法的跨音速透平叶栅速度面反问题设计方法。
In this paper the Direct Iterative Surface Curvature (DISC) design method is presented for designing airfoils at transonic speeds.
本论文采用直接表面曲率迭代方法(DISC)进行跨声速翼型设计。
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。
The variation finite element method (FEM) using the pseudo-potential function was presented for the simulation of transonic rotational flows.
本文运用赝势函数变分有限元方法数值模拟了绕翼型的跨音速有旋流动。
It enables NASA to create the operating conditions for large transport aircraft flying at transonic speeds of up to 1,440 kilometers per hour.
它使得NASA可以为大型运输航天飞机创造出运行条件，以每小时1,440公里的跨音速飞行。
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。
This paper describes the initial experimental results of aeroelastic instability of BF-1 rotors on a transonic axial compressor facility at BIAA.
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的实验研究工作。
Using the above method, numerical simulations are implemented for supersonic, transonic and subsonic flows around three-dimensional open cavities.
运用此方法，本文数值模拟了三维开式空腔的超声速、跨声速、亚声速流动。
Use this platform to optimize the blades of a NASA transonic single stage turbine, the bended stacking line and the profile of this transonic stator.
运用该平台对某NASA跨音速单级透平动静叶片及该透平静叶的叶型和弯积叠线进行多目标气动数值优化研究。
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。
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。
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