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.
在超声速或高超声速绕流中，一种很严重的脉动压力环境是由激波边界层相互作用引起的激波振荡。
One of the more severe fluctuating pressure environments encountered in supersonic or hypersonic flows is the shock wave oscillation driven by interaction of a shock wave with boundary layer.
该方法也可用于其他圆柱绕流问题。
This method can be used to other problems of flows around circular cylinder.
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.
青藏高原东北侧存在着中尺度地形绕流辐合现象。
The physical factor fields and the behavial law of mesoscale geographical convergence over the northeast of Qinghai-Xizang Plateau are analysed.
讨论了大攻角绕流的流动非对称性成因及相应研究对策。
Discussions are made on the cause leading to flow asymmetry in high alpha flows, and corresponding research strategy is proposed.
本文给出了一种多段翼型绕流的分区贴体网格生成方法。
A method has been developed which generates the body-fitted coordinates of multi-element airfoils by using of a grid patching technique.
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 Calculating method of inviscid steady transonic flow over wings is presented.
本文探讨了圆柱绕流脱落旋涡空间相关长度的测量技术。
In present paper, the correlation length measuring techniques of vortex shedding from a circular cylinder are studied.
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.
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.
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.
通过使用动网格技术，可实现对桥梁断面等刚体截面绕流场的模拟。
The moving grid technique is adopted to simulate the fluid fields around the rigid body such as bridge girder cross-sections.
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.
从全速位方程出发研究了机翼和翼身融合体跨音速绕流的有限元算法。
The finite element algorithm for transonic flows about wing and blended wing-body configuration is investigated based on the full potential equations.
有压管道中凸体绕流的势流一般解可采用解析函数在辅助平面上获得。
The general solution for potential flow past irregularities im a pressure conduit can be obtained in auxiliary plane by use of analytic functional theory.
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.
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.
对于旋成体有攻角绕流，本文研究了垂直于物面的横截面上的流态结构。
The topology of flow patterns on cross section perpendicular to the body surface are studied for flows around a body of revolution at angles of attack.
单元模块采用重力沉降、惯性阻挡、绕流阻留、离心力等多种除尘机理。
The unit modules adopt a plurality of dedusting mechanisms, such as gravity settling, inertia blocking, flow around retaining, centrifugal force, etc.
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.
考虑到非线性的自由液面边界条件，用下潜涡环栅格法求解水翼绕流问题。
The nonlinear free surface boundary condition is considered and the hydrodynamics forces of the hydrofoil near the free surface are calculated by the submerged vortex lattice method.
考虑到非线性的自由液面边界条件，用下潜涡环栅格法求解水翼绕流问题。
The nonlinear free surface boundary condition is considered and the hydrodynamics forces of the hydrofoil near the free surface are calculated by the submerged vortex lattice method.
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