脱体涡

本文发展了一种面元法（PanelMethod），用以计算具有脱体涡的三元厚度机翼的空气动力。

The present paper has developed a panel method predicting the non-linear aerodynamic loads on thick wings with separation vortices .

N-S方程数值模拟弹体不可压脱体涡绕流

N-S equation solutions for incompressible vortical flows over a tangent-ogive-cylinder

具有脱体涡的厚度翼绕流计算

Calculation of the flow around thick wings with separation vortices

三角翼前缘脱体涡和尾涡的卷起及其相互作用

The rolling-up and interaction of the leading-edge and trailing-edge vortex sheets of a delta wing

拟压缩性方法数值模拟绕弹体的不可压缩层流脱体涡流动

On the Method of Pseudo Compressibility for Numerical Solution of the Steady incompressible Laminar Vortical Flows over a Tangent-Ogive-Cylinder

背鳍对三角翼大迎角脱体涡的影响

Effect of Dorsal Fin Height on Symmetry and Asymmetry of Vortex Pairs over Delta Wing at High Angles of Attack

当背风区宽度已不能容其自由发展时，左右两侧脱体涡便互相推挤，致使较弱的脱体涡被上推，形成了不对称的涡迹。

When the width of leeside is not enough for the development of both side vortex , the weak vortex is pushed upward by the strong vortex .

本文描述的实验采用干冰为示踪粒子，对脱体涡系作了流动显示，并对摄取的图片进行了数字图象处理。

An experiment of using the dry ice as the tugged particle is described , and the flow visualization of the detached vones flow is discussed on the basis of digital image processing .

在非线性迎角范围内，雷诺数通过对机翼脱体涡和前机身体涡影响来改变飞机的纵向气动特性。

In the range of the nonlinear angles of attack , the longitudinal aerodynamic characteristics of aircraft is changed because of Reynolds number effects on the wing detached vortex and the front fuselage vortex .

进行双三角翼翼面流动显示研究的目的是为了揭示前、后翼脱体涡的干扰机理和详细结构，进而达到控制表面涡分离的目的，并为计算流体力学建立数学模型提供依据。

The purpose of flow visualization research of sections in double delta wing is to uncover the mechanism of vortex interference and structure , from this research , we can control the vortex and provide lasis for constructing numerical model .

从计算所得的表面摩擦应力线、空间流线和横截面流场特性，分析了10°≤α≤70°迎角范围内的分离和脱体涡系形态，算出了相应的气动特性。

From the computed skin friction lines , off surface streamlines and cross section streamlines , patterns of the 3D separation and the resulting vortices are analyzed for 10 ° ≤ α ≤ 70 ° . The aerodynamic characteristics are also computed against axes ratios .

该方法适用于翼面产生脱体涡流型或脱体涡占优（涡破裂前）所引起的非线性问题。

The method is only suitable for the nonlinear problem caused by detached vortex of wing before vortex breakdown .