The free vibration of a multi layered cylindrical shell submerged in an irrotational, inviscid and compressible fluid is studied.
研究了无旋、无粘、可压缩流体中多层圆柱壳的自由振动问题。
The inviscid and viscous flow physics around a high lift configuration and the complexity of its flow phenomena and the difficulty of its description are analyzed and discussed.
分析和讨论了高升力系统外形无黏和黏性流动的物理特征，表明了流动现象的复杂性和求解的艰难性。
Higher order waves generated by a moving source in a two-layer inviscid, incompressible fluid of finite depth with small density difference were studied.
研究了运动点源在无粘、不可压且具有小密度差的两层有限深流体中生成的高阶波动。
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 results show that the interaction between a viscous vortex ring and a free surface is different from the inviscid one.
结果表明：由于粘性的存在，使得涡环与自由表面的相互作用与无粘情形相比有许多不同。
A vortex panel method is presented to simulate low speed inviscid separated flow past an airfoil with a spoiler.
本文介绍用涡面元法模拟带扰流片的翼型低速无粘分离绕流。
In this paper the stability of a centrifuge rotor partially filled with an inviscid, incompressible liquid is analyzed experimentally.
本文对部分充有无粘不可压缩液体的离心机转子系统稳定性问题作了试验研究。
This paper presents a numerical analysis of inviscid equilibrium and nonequilibrium hypersonic flow past blunt-nosed slender cones.
本文给出钝头细长锥无粘、平衡和非平衡高超声速绕流流场的数值分析。
We investigate the linear stability of a shocked accretion flow onto a black hole with the following procedures: First, we study the stability in the inviscid isothermal limit.
我们按如下步骤研究了含激波的黑洞吸积流的线性稳定性问题：首先，我们研究无粘滞的等温吸积流。
Using the progressive iterative, the method allows direct extension of MFES to nonlinear inviscid compressible flow. Thus it provides a new approach to the solution of the nonlinear equations.
采用逐步逼近的办法，可以把有限基本解方法推广到求解非线性的无粘可压流体，从而为非线性方程的求解提供了新的途径。
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。
A numerical method for calculating steady inviscid transonic flows over wings is introduced in this paper.
本文介绍机翼无粘定常跨音速绕流的一种数值计算方法。
The forebody, suspension lines and canopy were modeled as a series of elastically connected mass nodes. The flow field inside the canopy was two-dimensional inviscid, incompressible flow.
前体、伞绳及伞衣离散为一系列弹性连接的质量节点，伞衣内部流场为二维无粘、不可压流。
The forebody, suspension lines and canopy were modeled as a series of elastically connected mass nodes. The flow field inside the canopy was two-dimensional inviscid, incompressible flow.
前体、伞绳及伞衣离散为一系列弹性连接的质量节点，伞衣内部流场为二维无粘、不可压流。
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