查询词典 transonic

Through solving the Navier-Stokes equation, three dimensional transonic unsteady flow in isolated rotor blade was simulated.

本文通过数值求解Navier-Stokes方程，计算了跨音速压气机转子叶排内三维非定常粘性流动。

At first, numerical simulation are made on the temporal developing gas-phase mixing layer where the convective mach number is in the region of subsonic(0.5) and transonic(0.8). For the temporal problem where Mc is 0.5, researches where the computational field contains different numbers of initial disturbances(so-called n period problem) are made respectively, and vortex's types of evolution in mixing layer including different numbers of initial disturbances are investigated; For the temporal problem where Mc is 0.8, the distinct shock let structure is obtained, and its mechanism is analyzed at the same time.

文中首先对对流马赫数为亚声速(0.5)、跨声速(0.8)的时间发展单气相混合层作了数值研究，对Mc为亚声速单气相时间发展混合层，分别研究了计算域包含不同数目的初始扰动周期问题，考查了不同周期数的混合层中涡的不同演化方式；对Mc为跨声速的单气相时间发展混合层，得到了清晰的小激波结构，同时分析了小激波的形成机理。

Analytical solutions for displacements of the viscoelatic half-space were obtained using Green's function method for various moving loads,including constant and harmonic point,line and area load.All velocity cases including the subsonic,transonic and supersonic velocities were considered.

首先采用Green函数法求解黏弹性半空间体在各种移动荷载模式作用下的动力响应的解析解，包括恒常和简谐移动点源、线源和面源荷载。

Thus it was extensively applied to experimental research of transonic and hypersonic flow.

因此，它在跨声速和超声速流的实验研究中得以广泛地应用。

Unlike in subsonic and transonic speed regimes, the interference resulting from the finite size of the test region is seldom present.

不像在亚、跨音速区域，这里因试验段尺寸有限造成的干扰是难得存在的。

Unlike in subsonic and transonic speed regimes, the in terference result in g from the f in ite size of the test region is seldom present

不像在亚、跨音速区域，这里因试验段尺寸有限造成的干扰是难得存在的。

Suitable for numerical simulation of subsonic、transonic and supersonic flow field of nozzle.

3适应于喷管内亚、跨、超音速流场的数值模拟。

Thirdly, the subsonic, transonic and supersonic flutter critical speed of wings and aircraft is numerically simulated. Some numerical results are in good agreement with experimental data.

分别以某后掠机翼和超临界机翼为算例，对机翼的静气动弹性问题以及基于静气动弹性的型架外形优化设计和飞行姿态确定进行研究，计算结果和有关文献的结果进行了比较，吻合很好。

Partial structure similarity model design concept is a better method for composite flutter model design, which can be applied to design transonic flutter model for aircraft wing and tail plane.

部分结构相似设计方法是一种较为实用的复合材料颤振模型设计方法，可用于飞机机翼、尾翼的跨声速颤振模型设计。

The numerical method for the unsteady transonic flow is presented in the third part of this thesis.

在第三部分中，根据前面所提出的求解Euler方程的方法，利用非定常问题的边界条件，建立了计算跨音速非定常流动的计算方法。

The split between the two groups can hardly be papered over.

这两个团体间的分歧难以掩饰。

This approach not only encourages a greater number of responses, but minimizes the likelihood of stale groupthink.

这种做法不仅鼓励了更多的反应，而且减少跟风的可能性。