球体规则绕流是没有升力的。
没有一个合适的端板尺寸将会阻止翼根绕流。
研究圆柱绕流中拉力系数的自适应计算问题。
We study adaptive computation of drag-coefficient of flow around a cylinder.
本文采用理想螺旋桨模型来简化螺旋桨绕流问题。
The ideal propeller model is used in this article to simplify the flow around the propeller.
振动圆柱绕流的一个重要特征就是出现锁定现象。
采用八叉树结构，生成复杂外形绕流计算的非结构直角网格。
Unstructured Cartesian grid for complex geometries is generated based on Octree data structure.
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。
A vortex panel method is presented to simulate low speed inviscid separated flow past an airfoil with a spoiler.
数值算例表明本方法是求解带襟翼偏转的机翼绕流的有效方法。
Numerical results show that the present method is effective one for solving the flow around wing with flap deflection.
本文分析了钝物体绕流的各种流动状态和相应的流致振动现象；
The flow around the bluff bodies and the related flow-induced vibrations are reviewed in this paper.
这与球体绕流(即绕球体的流动)的湍流转捩及分离流现象有关。
The ball and the flow around namely the flow around the sphere of turbulent flow and unprecedented turn phenomena.
数值算例表明本方法是求解带操纵面偏转的机翼绕流的有效方法。
Numerical results show that the present method is effective one for solving the flow around wing with control surface deflection.
数值算例表明该方法是求解带操纵面偏转的机翼绕流的有效方法。
Numerical results show that the present method is effective for solving the flow around a wing with control surface deflection.
在水洞实验台上进行了S型叶片绕流的实验观察与实验数据采集。
Experiment and data collection of flow status around S-shaped blade were performed on a water tunnel experiment rig.
因此对它的求解，要较相应另攻角轴对称绕流的二点边值问题简便。
Therefore, the solutions can be obtained more easily than that of two point boundary value problems of axisymmetric flow case.
研究了在大迎角下，后掠翼对细长体绕流结构和气动力特性的影响。
The influence on flow structure and aerodynamic of a slender by sweep wing at high Angle of attack was studied.
计算了圆柱的升阻力系数、尾涡脱落频率等描述绕流问题的主要参量。
Such parameters of flow characteristics are investigated as lift and drag coefficient and vortex shedding frequencies.
本文用H型网格和特殊的差分格式数值求解了粘性不可压缩叶型绕流。
The numerical solution of incompressible viscous flow over an aerofoil is obtained by H-type grids and a special difference scheme.
数值算例表明该方法是求解带操纵面偏转的翼身组合体绕流的有效方法。
Numerical results show that the present method is effective one for solving the flow around a wing body combination with control surface deflection.
本文提出了一种计算回转体定常。不可压缩粘性绕流问题的新数值方法。
This paper presents a new numerical method for calculating steady incompressible viscous flow around bodies of revolution.
提出了一种数值模拟振动的理想平板绕流场，并提取其气动导数的方法。
Numerical simulation of the flow field around the oscillating ideal flat plate is presented to assess the aerodynamic derivatives.
数值算例表明本文方法是求解带操纵面偏转的翼身组合体绕流的有效方法。
Numerical results show that present method is an effective one for solving the flow around wing body configuration with control surface deflection.
通过实例分析，证明这种方法对叶栅绕流等复杂流动现象的模拟是有效的。
Results reveal that the new method is effective for complex phenomenal simulation such as cascade flows.
“空气动力学”规定了由于绕流反作用在发射飞行器上存在的压力场和载荷。
"Aerodynamics" defines the pressure fields and loads that exist on a launch vehicle due to the reaction of ambient flow.
研究结果表明流体绕流振动圆管时，在较低流速下即可获得较好的传热效果。
The result shows that the preferable heat transfer effect can be acquired on the condition of a low flow rate.
在以上讨论和大量计算的基础上，本文最后给出了振动圆柱绕流的锁定区域。
Based on the above discussion and a great quantity calculation, the lock-in region of the flow about the oscillating cylinder was obtained.
本文应用绕流理论对圆柱形煤锭模型纵向绕流的受力在实验的基础上进行了分析。
This paper analyzes the pressure distribution around the stationary cylindrical Model based on the experiment using the theory of flow.
根据叶型表面的压力分布，着重分析了叶型的空气动力绕流和叶栅特性的变化规律。
According to the pressure distribution on the airfoil surface, analysis is made particularly of the airflow around the airfoil and of the variation law of cascade characteristics.
本文对均匀来流和剪切来流条件下，圆柱绕流及其电磁控制进行了实验和数值研究。
In this paper, the experimental and numerical investigations on electro-magnetic control of cylinder wake have been performed in this paper.
本文应用零方程模型和二方程模型计算了椭球体有攻角绕流对称面上的三维湍流边界层。
Revised method is proposed for calculation of three dimensional turbulent boundary layers on the surface of symmetry plane of a flow around ellipsoid at incidence.
本文应用零方程模型和二方程模型计算了椭球体有攻角绕流对称面上的三维湍流边界层。
Revised method is proposed for calculation of three dimensional turbulent boundary layers on the surface of symmetry plane of a flow around ellipsoid at incidence.
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