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
   形进气道 的翻译结果: 查询用时:0.01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
更多类别查询

图标索引 历史查询
 

形进气道
相关语句
  shaped inlet
     A practical engineering oriented algorithm based on multi grid technique is presented for computing full viscous internal flow in a S shaped inlet. The algorithm originates from Brandt′s multi grid theory and sloves 3 D Reynolds average N S equation with time marching implicit scheme of Beam Warming from fine grid levels through coarse ones in conjunction with“saw”shape iteration.
     提出了一种基于多重网格技术,可快速求解S形进气道粘性内流场的实用工程算法:从Brandt的多重网格理论出发,采用隐式Beam-Warming时间推进格式,结合“锯齿式”迭代技术交替在粗、细两种网格上对雷诺平均三维非定常N-S方程进行求解。
短句来源
  “形进气道”译为未确定词的双语例句
     ENGINE/S-SHAPED-INLET COMPATIBILITY
     S形进气道和发动机相容性
短句来源
     Calculation of Boundary Layer of a Three Dimensional S-Shaped Inlet
     S形进气道附面层计算
短句来源
     A STUDY ON HIGH SUBSONIC S-SHAPED INLETS IN MISSILES
     弹用高亚音速S形进气道设计和试验研究
短句来源
     Numerical simulation of flow field for supersonic S-shaped inlet
     S形进气道流场数值模拟
短句来源
     A Numerical Simulation Investigation of Flow Characteristics for Short-S Inlet Ducts
     短S形进气道流动特性数值模拟研究
短句来源
更多       
  相似匹配句对
     ENGINE/S-SHAPED-INLET COMPATIBILITY
     S进气道和发动机相容性
短句来源
     The configure of the inlets is "X" type with square section.
     进气道为方截面X布局。
     Shape * Shadow
     *影
短句来源
     Numbers and Figures
     数与
短句来源
     Forming Technique of Air Intakes Made of Glass fiber Reinforced Plastics
     玻璃钢进气道成型工艺
短句来源
查询“形进气道”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。
  shaped inlet
The method uses a vacuum to withdraw a stream of gas-liquid dispersion from the bubble or foam column through a capillary tube with a funnel-shaped inlet.
      
Pulse-shaped inlet boundary conditions were assigned to simulate the dynamic tire loading on the asphalt pavements.
      
To sample aerosols, the air inlet valve is opened and air is drawn into the 3603 sandwich-shaped inlet.
      


The paper presents the results of measurement of the static pressure and swirl in the flow through an S-shaped duct of typical air intake proportions mounted in a wind tunnel and tested at different incidence.In order to reduce the magnitude of swirl at high incidence,two methods have been studied-one,to change the distribution of pressures by means of a spoiler and two,to re-energize the separated flow with an inflow of free stream air through auxiliary inlets.The results show a small degree of swirl at low...

The paper presents the results of measurement of the static pressure and swirl in the flow through an S-shaped duct of typical air intake proportions mounted in a wind tunnel and tested at different incidence.In order to reduce the magnitude of swirl at high incidence,two methods have been studied-one,to change the distribution of pressures by means of a spoiler and two,to re-energize the separated flow with an inflow of free stream air through auxiliary inlets.The results show a small degree of swirl at low incidence which takes the classical pattern of two contra-rotating flows,and a large degree of swirl at high incidence,in the form of a single rotating flow.Of the anti-swirl devices,the spoiler is the more powerful and can be sized either to reverse the swirl direction or to eliminate the swirl completely.A parameter of swirl coefficient,SC60,has been suggested,Values of SC60 at 30°incidence are 0.188 for the duct as designed,0.068 for the arrangement with auxiliary inflow and-0.039 with a spoiler of width 0.15 times throat width.The various arrangements tested,together with results of an earlier study,shed useful light on the general nature of swirl in an S-ductp its method of generation and its final form and magnitude.

本文给出了具有典型飞机进气道比例的S形管道在不同攻角下,压力分布和旋流的实验结果。为了减小大攻角下的旋流,研究了两种方法:一是通过扰流板改变管道内气流的压力分布,二是通过辅助进气门引入自由流空气,向分离流补充能量。结果表明,在低攻角下旋流很弱并呈现为典型的反向旋转对涡二次流动,而在高攻角下则为一个很强的单涡旋转流动。至于反旋流措施,扰流板的效果最好,通过变化其尺寸不仅能改变旋流方向,而且还可完全消除旋流。本文建议用一个旋流系数,SC_(60),来描述名义发动机进口处的旋流。其值对原设计模型在30°攻角时为0.188,而通过辅助进气门引入自由流空气向分离流补充能量后为0.068,当采用一个0.15倍喉道宽度的扰流板时,旋流系数变为-0.039。本研究使S形进气道中旋流的产生、发展和性质得到进一步的认识。

A mixed finite difference method for calculating the external and internal transonic flow field around a s-shaped inlet is presented. The equation of the full velocity potential in cartesian or cylindrical coordinates is used as the governing equation. As the method used for the present analysis separates coordinate system and the geometry, the mesh points may not lie on the body surface. The boundary Condition is satisfied by the mesh points which are situated in the vicinity of the wall. An improved analytical...

A mixed finite difference method for calculating the external and internal transonic flow field around a s-shaped inlet is presented. The equation of the full velocity potential in cartesian or cylindrical coordinates is used as the governing equation. As the method used for the present analysis separates coordinate system and the geometry, the mesh points may not lie on the body surface. The boundary Condition is satisfied by the mesh points which are situated in the vicinity of the wall. An improved analytical continuation method is developed to treat the boundary condition at solid face. A linear under-relaxation procedure is used in calculation. The relaxation process is marched forward axially from one part to another in sequential order. Calculation is repeated until the. change in velocity potential between relaxation sweeps is less than a preassigned value and the conservation of mass flow between cross sections in inlet is reached.Computations have been made for a s-shaped inlet with free stream Mach number M=0.8 at different angles of attack and at angle of yaw. Computed results are compared with those computed by perturbation, method and with experimental results. Such a comparison shows that the present method is promising.

提出了一种计算跨音速S形进气道内外流场的混合差分方法.该法从速势方程出发,利用直角和圆柱坐标系、不旋转的混合差分格式以及边界的解析延拓处理,建立了流场内各网格点的差分方程,并用线松弛法进行统一迭代.计算了一个S形进气道在来流马赫数为0.8以及不同攻角状态下的内外流场,并将计算结果与摄动法计算结果以及实验值进行了比较.

In the case of shielded s-shaped inlels,the internal and external three-

由于飞行器前部及进气道流动的相互影响,使腹部进气 S 形进气道三元跨音速内外流场变得非常复杂,不仅如此,所研究物体的复杂外形增加了差分格式和边界条件处理的困难,由于以上原因,腹部进气 S 形进气道的流动计算常难以收敛。

 
<< 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形进气道的内容
在知识搜索中查有关形进气道的内容
在数字搜索中查有关形进气道的内容
在概念知识元中查有关形进气道的内容
在学术趋势中查有关形进气道的内容
 
 

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