助手标题  
全文文献 工具书 数字 学术定义 翻译助手 学术趋势 更多
查询帮助
意见反馈
   非对称涡 的翻译结果: 查询用时:1.116秒
图标索引 在分类学科中查询
所有学科
航空航天科学与工程
力学
更多类别查询

图标索引 历史查询
 

非对称涡     
相关语句
  asymmetric vortices
     Study on Control Mechanism of Asymmetric Vortices over Slender Body Using MEMS Device
     基于MEMS的细长体非对称涡控制机理研究
短句来源
     SMOG VISUALIZATION TECHNIQUE OF ASYMMETRIC VORTICES ON FOREBODY AT HIGH WIND SPEED
     前体非对称涡高风速烟雾显示技术
短句来源
     Numerical Simulation and Calculation of the Effect of Asymmetric Vortices for Spinning WingBodyTail Combination
     旋转翼-身-尾组合体非对称涡效应的数值模拟与计算
短句来源
     Experimental study of Reynolds numbers effect on asymmetric vortices and their aerodynamic characteristics over a slender body
     Re数对细长旋成体非对称涡及气动力特性影响的实验研究
短句来源
     The research indicated that MEMS device generate excellent control effect on asymmetric vortices over slender body as well as on complex flow field.
     研究表明:MEMS器件对控制大迎角细长旋成体非对称涡和复杂流场具有良好的控制能力。
短句来源
更多       
  asymmetric vortex
     On the Numerical Simulation of Asymmetric Vortex Shedding about Viscous Flow over a Circular Cylinder
     圆柱绕流非对称涡发放的数值模拟
短句来源
     Research of asymmetric vortex characteristic about forebody of slender wing and body
     细长翼身组合体前体非对称涡特性研究
短句来源
     The asymmetric vortex structure of the slender cylindrical body growing gradually along the symmetry axis of the slender body is shown.
     同时讨论了大迎角旋成体背涡生成和发展情况,给出该状态非对称涡的结构模型。
短句来源
     Angle of attack and nose shape of bodies are key factors that asymmetric vortex occurs over slender bodies.
     迎角、旋成体的外形,尤其是头部的几何形状是细长前体出现非对称涡的关键因素。
短句来源
     It is believed that the asymmetric vortex generates at the nose of a revolution.
     通过数值模拟揭示了在头部开始产生非对称涡,形成二次涡的机理以及在背风侧形成集中涡的过程。
短句来源
  “非对称涡”译为未确定词的双语例句
     Experimental investigation of asymmetry vortex unsteadiness over slender cylinders
     绕细长旋成体非对称涡非定常性的实验研究
短句来源
     Simulation experimental technique and primary study of Reynolds number effect on vortex asymmetry at forebody
     前体非对称涡Re效应初探及其风洞模拟技术
短句来源
     The results of wind-tunnel experiments and laser vapour screen flow observation proved the configuration to be effective. An unsteady region during the transition of symmetric vortices to asymmetric ones was discovered.
     实验发现由对称涡向非对称涡的转变有一个不稳定区,建议用动态测力,得到与激光蒸汽屏流场相一致的结果,并研究其相互关系。
短句来源
     Effectiveness of the fast swinging micro tip strake technique for controlling forebody vortex asymmetry at high angles of attack has been investigated and de veloped in low speed wind tunnel experiments on a slender body of revolution wi th pointed nose configuration.
     研制了一种新的大攻角细长旋成体非对称涡的主动控制技术 ,即在细长旋成体头部施加非定常弱扰动来控制头部非对称背涡。
短句来源
     For steady asymmetric vortical flow, study shows that the side force on after cylinder induced by asymmetric nose vortices is significantly weakened, because of boundary layer separation on after body is blocked by section of wingbody combination, and also shows that the outplane force on wingbody combination with "○"configuration is larger than those on body alone.
     研究表明,在大迎角定常非对称涡的范围内,由于翼身组合段对后柱体的边界层分离起遮蔽作用,大大削弱了非对称头涡在后柱体上诱导的侧力。 实验证实,平置式翼身组合体的侧力要比单独体的侧力大;
短句来源
更多       
查询“非对称涡”译词为用户自定义的双语例句

    我想查看译文中含有:的双语例句
例句
为了更好的帮助您理解掌握查询词或其译词在地道英语中的实际用法,我们为您准备了出自英文原文的大量英语例句,供您参考。
  asymmetric vortices
Influence of nose perturbations on behaviors of asymmetric vortices over slender body
      
The influence of nose perturbations on the behaviors of asymmetric vortices over a slender body with a three-caliber ogive nose is studied in this paper.
      
The effect of the perturbation axial location on asymmetric vortices is the strongest if its location is near the model apex.
      
Various types of perturbation do not change the perturbation effect on the behaviors of bistable asymmetric vortices.
      
Asymmetric vortices flow over slender body and its active control at high angle of attack
      
更多          
  asymmetric vortex
Static properties of asymmetric vortex-like domain walls in magnetically uniaxial thick films
      
It is established that the asymmetric vortex-like domain walls are the most universal wall structures in the films under consideration.
      
In the turning region, a pair of Dean vortices shown in the stationary case transform into one large asymmetric vortex cell, and subsequently heat/mass transfer and pressure drop characteristics also change.
      
The flow is quite sensitive to directional perturbations, with even slight inclinations of the jet with respect to the counterflow resulting in regular asymmetric vortex shedding and a decreased mean downstream extent.
      
Numerical investigation of the mechanism of asymmetric vortex flows
      
更多          
  forebody asymmetric vortices
This paper attempts to provide an update state of art to the investigations on the fields of forebody asymmetric vortices.
      
  asymmetric vortices flow
Asymmetric vortices flow over slender body and its active control at high angle of attack
      
The studies of asymmetric vortices flow over slender body and its active control at high angles of attack have significant importance for both academic field and engineering area.
      


Flow pattern visualizations and surface pressure measurements on a slender body witb two different elliptical cross-section noses were conducted at sideslip and high angle of attack condition, under which the body generates an asymmetric vortex system. The mechanism of how a flattened nose shape can contribute the directional stability to the slender body fitted with various noses at high angle of attack has been investigated and revealed by analyzing and comparing the flow patterns, the cross-sectional pressure...

Flow pattern visualizations and surface pressure measurements on a slender body witb two different elliptical cross-section noses were conducted at sideslip and high angle of attack condition, under which the body generates an asymmetric vortex system. The mechanism of how a flattened nose shape can contribute the directional stability to the slender body fitted with various noses at high angle of attack has been investigated and revealed by analyzing and comparing the flow patterns, the cross-sectional pressure and the side force distributions along axis of bodies.

本文对两种椭圆截面头部细长机体在大迎角侧滑下的非对称涡系进行了流态垦示和表面压强分布测量。通过对不同头部机体的流态、截面压强分布及沿轴线的侧力分布之分析和比较,研究和揭示了为什么扁平形状的头部能在大迎角下提供航向稳定性的机理。

This paper studies the phenomenon of off-surface forces and moments due to asymmetric vortices on a cylindrical body with ogive nose at high angles of attack in subsonic and transonic flows.Methods to allev'iate those undesirable forces and moments are discussed.An appropriate nose configuration was designed and tested.The results of wind-tunnel experiments and laser vapour screen flow observation proved the configuration to be effective.An unsteady region during the transition of symmetric vortices to asymmetric...

This paper studies the phenomenon of off-surface forces and moments due to asymmetric vortices on a cylindrical body with ogive nose at high angles of attack in subsonic and transonic flows.Methods to allev'iate those undesirable forces and moments are discussed.An appropriate nose configuration was designed and tested.The results of wind-tunnel experiments and laser vapour screen flow observation proved the configuration to be effective.An unsteady region during the transition of symmetric vortices to asymmetric ones was discovered.

本文提出了一个消除非对称力的头部外形方案。通过风洞实验,论证了方案是有效和稳定的。实验发现由对称涡向非对称涡的转变有一个不稳定区,建议用动态测力,得到与激光蒸汽屏流场相一致的结果,并研究其相互关系。

The viscous flow around a rectangular cylinder is simulated by solving the two dimensional compressible Navier-Stokes equations. The partial differential equations are approximated by difference methods such as special chosen Jacobian matrix splitting technique and approximate factorization. The scheme has second order accuracy in space and time. The Mach number Ma =0.3 and the Reynold number Re = 20000 are used in the computation. The unsteady Karman vortex separation and asymmetry of pair of vortices can be...

The viscous flow around a rectangular cylinder is simulated by solving the two dimensional compressible Navier-Stokes equations. The partial differential equations are approximated by difference methods such as special chosen Jacobian matrix splitting technique and approximate factorization. The scheme has second order accuracy in space and time. The Mach number Ma =0.3 and the Reynold number Re = 20000 are used in the computation. The unsteady Karman vortex separation and asymmetry of pair of vortices can be seen clearly from the computed results, The old vortices are moved downstream and the new ones are generated from the corner of the cylinder. The influence of compressibility on vortex formation is considered. The critical Reynold number Rec is increased with the Mach number increased.

采用近似因式分解和特殊Jacobin系数矩阵分裂法,求解可压缩Navier-Stokes方程,数值模拟矩形柱体绕流流场中分离涡的形成和发展。给出了Ma_∞=0.3,0.8;Re=10~4,10~6的计算结果。从结果中可清楚地看到柱体非对称涡形成的非定常过程。

 
<< 更多相关文摘    
图标索引 相关查询

 


 
CNKI小工具
在英文学术搜索中查有关非对称涡的内容
在知识搜索中查有关非对称涡的内容
在数字搜索中查有关非对称涡的内容
在概念知识元中查有关非对称涡的内容
在学术趋势中查有关非对称涡的内容
 
 

CNKI主页设CNKI翻译助手为主页 | 收藏CNKI翻译助手 | 广告服务 | 英文学术搜索
版权图标  2008 CNKI-中国知网
京ICP证040431号 互联网出版许可证 新出网证(京)字008号
北京市公安局海淀分局 备案号:110 1081725
版权图标 2008中国知网(cnki) 中国学术期刊(光盘版)电子杂志社