也就是说，缺乏横向稳定器尾节，所以研究人员可以测试的理论，这些成分在跨音速的速度在稳定问题的关键因素增长约0.9马赫。
That is, the tail section lacked horizontal stabilizers, so researchers could test a theory that those components were a key factor in stability problems at transonic speeds up to about Mach 0.9.
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。
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。
The variation finite element method (FEM) using the pseudo-potential function was presented for the simulation of transonic rotational flows.
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 implicit time-marching method is presented for solving the transonic Euler equations.
文中还提出了压气机叶栅在高亚音速、跨音速工作条件下，修正气体压缩性影响的新的图线方法。
In this paper, a new curvilinear method for correcting the gaseous compressible effect under higher subsonic and transonic intake condition upstream of the cascade is. presented.
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。
An iteration method is used for computing the transonic pressure distribution on a flexible wing.
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。
Several computed results of transonic turbine cascades are presented to illustrate the method's capabilities.
分别对可压缩叶栅流场的亚音速和跨音速流动进行了数值模拟计算。
Some cases of compressible flow as well as incompressible flow are presented.
提出了一种可解决超音速、亚音速、跨音速、冲击波共存的流场计算方法，即变形流体网格两步法。
The paper presents a new computational method named two steps various shape FLIC method, applied for the existence of the supersonic , sub critical sonic , transonic, shock wave.
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 paper describes experimental flow study results of trailing edges of transonic turbine blades in a closed transonic wind tunnel with discussing its mechanism.
给出一种新的二维跨音速柔性自适应壁风洞实验迭代方案，计算方法和实验验证结果。
In this paper, a new iterative testing strategy is described for two dimensional model testing in transonic flexible adaptive walled wind tunnel and wall adjustment computing method.
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 transonic flow field around NACA 0012 airfoil is calculated by finite element method from pressure minimum integration, full potential equation being used.
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。
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.
通过数值求解定常跨音速流的无粘、小扰动方程，根据实心翼型或多孔翼型的边界条件，获得了相应的压力分布。
By numerically solving the inviscid, small disturbance equation in steady transonic regime, with boundary conditions on solid or porous airfoils, the corresponding pressure distribution is obtained.
如果有合适的发动机的话，这种结构可以提供良好的持续性超音速巡航能力，以及良好的跨音速和超音速机动能力。
This configuration will provide good sustained supersonic cruise performance with a suitable engine type, and good manoeuvre performance in transonic and supersonic regimes.
低能量损失系数跨音速透平叶栅的设计和实现是提高跨音速透平性能的关键问题之一。
The design and realization of a transonic turbine cascade with low energy loss is one of the crucial problems which should be solved for designing good transonic turbines.
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。
It enables NASA to create the operating conditions for large transport aircraft flying at transonic speeds of up to 1,440 kilometers per hour.
然后采用IFFT算法和自适应数值积分算法计算二维积分，得到了低音速、跨音速和超音速移动荷载作用下动力响应的数值结果。
Coupled IFFT algorithm and adaptive quadrature algorithm was employed to compute double integrals in the analytical solutions. All the subsonic, transonic and supersonic cases were computed.
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。
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.
本文研究了机翼跨音速颤振的频域计算方法。
Computation of wing flutter for unsteady transonic flows in the frequency domain is studied in this thesis.
本文采用全位势方程，在超音速区采用虚拟气体假设，给出了跨音速无激波翼型设计的一种方法。
In this paper, a method for the transonic shock-free airfoil design, based on the full potential equation, using "fictitious gas" assumption, is presented.
本课题以某型压气机的跨音速叶栅为研究平台，以提高叶栅静压增压比，减少叶栅流动损失为目标。
This thesis investigated transonic cascade of a certain compressor in order to increase the static pressure ratio of the cascade and reduce the coefficient of the cascade losses.
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。
This paper deals with the inverse design problem of transonic turbine cascade in the hodograph plane by the finite area method.
进行了多级跨音速风扇粘性流动的数值模拟研究。
Numerical simulation of viscous flows through multistage transonic fans was carried out.
本文介绍机翼无粘定常跨音速绕流的一种数值计算方法。
A numerical method for calculating steady inviscid transonic flows over wings is introduced in this paper.
其结论对改善跨音速风洞设计和模型试验是有用的。
The conclusions believed to be useful to improve the design of transonic wind tunnel and model tests.
气水模拟方法对跨音速叶栅的方案设计和定性分析具有正确、直观、简便、经济的优点。
The shallow water through analogy has advantages of exactness, visualization, simplicity and economy valuable in the concept design and qualitative analysis stage of transonic turbine cascades.
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。
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.
计算得到了NASA37号低展弦比、跨音速轴流压气机级70％设计转速下的全工况性能曲线，并重点分析了其中一些典型工况下的内部流场。
The overall performance for NASA 37 low-aspect ratio compressor stage at 70% design rotating speed was obtained and the internal flow fields at typical operating conditions were emphatically analyzed.
计算得到了NASA37号低展弦比、跨音速轴流压气机级70％设计转速下的全工况性能曲线，并重点分析了其中一些典型工况下的内部流场。
The overall performance for NASA 37 low-aspect ratio compressor stage at 70% design rotating speed was obtained and the internal flow fields at typical operating conditions were emphatically analyzed.
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