跨声速无粘流用全速势方程模拟。
The inviscid flow is obtained by the numerical solution of fully potential equation.
这一特征对跨声速流动中的若干结果有一定概括性。
This characteristic is some summary to a certain number of results obtained in transonic flow study.
讨论应用线性和非线性涡粘性湍流模式计算跨声速湍流 。
Study of separated flow in a diffuser using linear and nonlinear eddy-viscosity turbulence models;
讨论应用线性和非线性涡粘性湍流模式计算跨声速湍流 。
The comparison of turbulence models applied to viscous ship flow computation;
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。
A numerical method is presented for predicting unsteady transonic aerodynamic flow about aircraft wings with control surface.
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。
In this paper the Direct Iterative Surface Curvature (DISC) design method is presented for designing airfoils at transonic speeds.
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。
This paper represents a CFD method for the design of NLF airfoils directly under transonic viscous flow conditions.
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。
Coupled with the structural equations, the models for transonic aeroelasticity in state-space are got.
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。
Using the above method, numerical simulations are implemented for supersonic, transonic and subsonic flows around three-dimensional open cavities.
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。
An improved streamline curvature numerical method is modified and applied to better approximate the flow fields of multi-stage transonic axial compressors.
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。
Numerical analyses of the transonic nozzle inviscid flow and supersonic jet impingement on a jet TAB are presented.
在亚跨声速时分别采用了表面积分和尾迹积分求得给定翼型RAE2822的阻力。
Predicted drag values for a given airfoil(RAE2822 airfoil)were compared and discussed using the surface integration and wake integration methods under both subsonic and supercritical flow conditions.
作为算例，对伴有激波的方形收放喷管跨声速流动进行了计算，以显示方法的有效性。
A numerical example for the transonic flows with shock wave in the converging-diverging square nozzle is used to indicate the effectiveness of this scheme.
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。
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.
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 effect of acoustic excitation on the flow asymmetry over a slender body in compressible flows was investigated in a transonic wind tunnel.
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。
The new method is used to study transonic flow in cascades and one kind of complex unsteady transonic axisymmetric flow in arc breaker.
本文介绍用低超声速喷管代替声速喷管，解决了大迎角大堵塞度跨声速实验时的风洞壅塞问题。
Instead of the sonic nozzle, low supersonic nozzles have been utilized to solve the choking problem in transonic wind tunnel testing of high angle-of-attack and high blockage.
传统的阵风响应主要在频域内进行分析，气动载荷基于线性方法计算，不能考虑黏性和跨声速流动影响。
Traditional gust responses are mainly analyzed based on linear aerodynamic load calculations in frequency-domain, which is unsuitable for and the viscous and transonic flows.
本文采用二维可压缩非定常N-S方程模拟了带有上下开槽壁的跨声速二维管风洞中超临界翼型绕流的流场。
Transonic tube wind tunnel flows over supercritical airfoils with slots on both upper and lower walls have been simulated by using compressible unsteady two dimensional Navier-Stokes equations.
采用C-H型网格、守恒型非定常全位势方程的时间精确近似因式分解差分法计算二维、三维的跨声速非定常位势流。
The conservative full potential equation and C H grid are used to compute the unsteady transonic flows around airfoils and wings.
采用新建立的试车台数据实时采集与监控系统，测量了该单级跨声速风扇的总性能和采用处理机匣后风扇的总性能、基元级性能。
By using real time data gathering and test system of the aero engine test bed, the detail measurement of single stage transonic fan performance with and without different casing treatments were made.
通过跨声速标模算例AGARD445.6机翼的颤振计算，计算的颤振临界速度与实验值有5%左右的误差，验证本方法的正确性。
The computing AGARD445.6 wing flutter results validate the physical law of a typical transonic flutter "dip" with the bottom near the domain which Mach number is 1.
对跨声速飞机机翼作了跨声速非定常气动力计算，对跨声速民航机机翼的颤振模型作了颤振计算，与TDLM的比较表明，两者结果有较好的一致性。
The unsteady aerodynamic results of the transonic wing are presented, and flutter calculation is made. The comparison with TDLM shows that the agreement is very good.
对跨声速飞机机翼作了跨声速非定常气动力计算，对跨声速民航机机翼的颤振模型作了颤振计算，与TDLM的比较表明，两者结果有较好的一致性。
The unsteady aerodynamic results of the transonic wing are presented, and flutter calculation is made. The comparison with TDLM shows that the agreement is very good.
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