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
   收敛形进气道 的翻译结果: 查询用时:0.287秒
图标索引 在分类学科中查询
所有学科
力学
航空航天科学与工程
更多类别查询

图标索引 历史查询
 

收敛形进气道
相关语句
  convergent inlet
     Verification of the numerical investigations of convergent inlet
     收敛形进气道数值研究的验证(英文)
短句来源
     The results of numerical and experimental studies of a new configuration of 3D hypersonic inlet with the minimum throat area,which was called a convergent inlet,are presented in this paper.
     介绍一种新型的、具有最小喉道面积的三维高超声速进气道 (称之为收敛形进气道 )的数值和实验研究结果。
短句来源
     The numerical algorithm was verified by calculated and experimental data for a finite width wedge and extemal compression surface of a convergent inlet.
     数值算法是通过收敛形进气道的有限宽楔形外压缩表面的计算和实验数据来验证的。
短句来源
  相似匹配句对
     Verification of the numerical investigations of convergent inlet
     收敛进气道数值研究的验证(英文)
短句来源
     ENGINE/S-SHAPED-INLET COMPATIBILITY
     S进气道和发动机相容性
短句来源
     S_n∈L_1, then S_n converges almost surely.
     s. 收敛
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。
     C -Mutiplier Convergence
     C-乘数收敛
短句来源
查询“收敛形进气道”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。
  convergent inlet
The results of numerical and experimental studies of a new configuration of 3D hypersonic inlet with the minimum throat area, which was called a convergent inlet, are presented in this paper.
      
The experiments were carried out on the three-dimensional convergent inlet model with and without sidewalls.
      


The results of numerical and experimental studies of a new configuration of 3D hypersonic inlet with the minimum throat area,which was called a convergent inlet,are presented in this paper.It is shown that the use of this inlet configuration allows one to reduce the drag and thermal protection of surfaces of a hypersonic engine within the entire range of flight velocities.This is achieved by decreasing the inclination of extemal compression surfaces and reducing the area of the inlet duct and combustor walls.The...

The results of numerical and experimental studies of a new configuration of 3D hypersonic inlet with the minimum throat area,which was called a convergent inlet,are presented in this paper.It is shown that the use of this inlet configuration allows one to reduce the drag and thermal protection of surfaces of a hypersonic engine within the entire range of flight velocities.This is achieved by decreasing the inclination of extemal compression surfaces and reducing the area of the inlet duct and combustor walls.The inlet configuration was constructed on the basis of gas dynamic design methods using the flows of lower dimension.The calculations were performed within the framework of inviscid gas model by the method of finite volumes.The flow and inlet characteristics,taking account of viscosity,were also calculated using the boundary layer equations.The numerical algorithm was verified by calculated and experimental data for a finite width wedge and extemal compression surface of a convergent inlet.The experimental studies were performed within the Mach number range from 2 to 10.7 and Reynolds number based on the model inlet height of Re=(1~5)10 6. The numerical and experimental results are in good agreement.These results are also compared with the data for traditional 2D inlets.

介绍一种新型的、具有最小喉道面积的三维高超声速进气道 (称之为收敛形进气道 )的数值和实验研究结果。表明使用这种形式的进气道 ,在整个飞行速度范围内可以降低阻力和高超声速发动机表面的热防护要求 ,通过降低外压缩表面的倾斜度和减少进气道及燃烧室壁的面积就可以做到这一点。在采用低维次流动的气体动力设计方法的基础上设计成这种形式的进气道。计算是在无粘气体模型构架内用有限体积法进行的。同时用边界层方程计算出计及粘性的气流特性和进气道特性。数值算法是通过收敛形进气道的有限宽楔形外压缩表面的计算和实验数据来验证的。进行实验研究的马赫数M=2~ 1 0 7,基于模型进气道高度的雷诺数Re=( 1~ 5) × 1 0 6。数值计算与实验结果一致性很好。这些结果也和通常的二维进气道的数据作了比较。

 
图标索引 相关查询

 


 
CNKI小工具
在英文学术搜索中查有关收敛形进气道的内容
在知识搜索中查有关收敛形进气道的内容
在数字搜索中查有关收敛形进气道的内容
在概念知识元中查有关收敛形进气道的内容
在学术趋势中查有关收敛形进气道的内容
 
 

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