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
   pressure 在 航空航天科学与工程 分类中 的翻译结果: 查询用时:0.164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
心血管系统疾病
石油天然气工业
物理学
气象学
自动化技术
燃料化工
有机化工
军事医学与卫生
更多类别查询

图标索引 历史查询
 

pressure
相关语句
  压强
    TRANSONIC PRESSURE DISTRIBUTION COMPUTATIONS OF A FLEXIBLE WING
    弹性机翼的跨音速压强分布计算
短句来源
    MEASUREMENTS OF UNSTEADY PRESSURE DISTRIBUTION ON A NACA 0012 PROFILE IN TRANSONIC FLOW
    NACA 0012翼型跨音速非定常压强分布的测量
短句来源
    FINITE ELEMENT METHOD FOR CALCULATING TRANSONIC POTENTIAL FLOW AROUND AIRFOIL FROM PRESSURE MINIMUM INTEGRATION
    计算翼型跨音速有势绕流的压强极小积分有限元法
短句来源
    The Effects of Burning Rate Catalysts on the Energy and Pressure Exponents of NEPE Solid Propellant
    燃速催化剂对NEPE固体推进剂能量和压强指数的影响
短句来源
    A STABLE COMBUSTION MODEL FOR COMPOSITE SOLID PROPELLANT WITH POSITIVE OR NEGATIVE BURNING-RATE PRESSURE EXPONENT
    呈正、负压强指数的复合固体推进剂稳态燃烧模型
短句来源
更多       
  “pressure”译为未确定词的双语例句
    Fatigue Reliability Analysis of Aeroengine Low Pressure Compressor Disk
    某型航空发动机低压压气机轮盘疲劳可靠性分析
短句来源
    ON THEORY OF UNSTEADY DECOMPOSITION COMBUSTION FOR A LIQUID MONOPROPELLANT DROPLET AT HIGH TEMPERATURE AND HIGH PRESSURE
    液体单元推进剂滴的高温高压非定常分解燃烧理论
短句来源
    THE EFFECTS OF RDX/AP PROPORTION ON HTPB COMPOSITE PROPELLANT COMBUSTION PROPERIES AT LOW PRESSURE
    RDX/AP配比对HTPB复合推进剂低压燃烧性能的影响
短句来源
    DEFORMATION AND BURST STRENGTH OF GFRP OYLIDERS UNDER INTERNAL PRESSURE
    玻璃钢圆筒壳体内压下的变形及破坏强度
短句来源
    The Equations of Thermodynamic Properties for Low Pressure Water / Steam and Their Application
    低压水和水蒸汽热力学性质方程及应用
短句来源
更多       
查询“pressure”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。
  pressure
In this article we investigate the asymptotic behavior of and using the dynamical system techniques: the pressure function and the variational principle.
      
An algorithm to calculate the pressure is presented.
      
The reported method1 of their synthesis involves hydrogenation at high temperature and pressure.
      
Invariant of topological pressure under some semi-conjugates
      
In this paper, the topological pressure is preserved under some semi-conjugates, and a formula of computing topological pressure by use of periodic points for positively expansive continuous map with specification is given.
      
更多          


A method of designing optimum wall contour for an supersonic exhaust nozzle is dealt with in this article. Through the adoption of this method, there will be obtained the optimum wall contour of an exhaust nozzle to yield maximum thrust under given nozzle length, ambient pressure, throat area and the flow conditions in the immediate vicinity of the throat. An assumption is made that the exhaust gas is perfectly ideal, and the gas flow within the nozzle is isentropic.

本文提出一种设计超音速推力喷管的方法。根据这种方法,可以在给定的喷管长度、外界气压、喉道面积以及喉道附近气流流动等条件下,设计出具有最大推力的超音速喷管管壁的形状。在分析喷管内气体的流动时,假设工作气体是完全的理想气体,气体的流动是等熵位流。

This paper presents a method of calculating the pressure distribution, lift, drag and pitching moment on cambered fuselage of arbitrary cross section at angle of attack by using the method of approximate conformal transformation within the limits of the slender theory. The present method is applicable to supersonic and subsonic.The arbitrary cross section may include local deformation region on fuselage, for example, nacelle and cowling attached to the fuselage, etc.The formulae of lift and drag presented...

This paper presents a method of calculating the pressure distribution, lift, drag and pitching moment on cambered fuselage of arbitrary cross section at angle of attack by using the method of approximate conformal transformation within the limits of the slender theory. The present method is applicable to supersonic and subsonic.The arbitrary cross section may include local deformation region on fuselage, for example, nacelle and cowling attached to the fuselage, etc.The formulae of lift and drag presented in this paper are connected withthe form in the proximity of the base of the body only, in consequence, it iseasy to calculate.A routine is made by using ALGOL-60 language according to the present method.

本文在细长体理论范围内应用近似保角映射方法解决了具有弯度、迎角、任意横截面机身的压强分布、升力、力矩等气动力问题。本文方法适用于超、亚音速。 任意横截面可似包括机身上有局部变形的区域,例如机身上的短舱、整流罩等。 本文提供的升力和阻力公式仅与机身底部附近的形状有关,因此是很便于计算的。 按本文方法已编制成ALGOL-60语言源程序。

Introduced in this paper is a new method by which the camber line of the turbine blade profile is described by a number of high order polynomial function sections, and which ensures the absence of flex point that is usually accompnied with that function. The paper offers to give a'description of the radius of the inscribed circles of the profile by a number of high order polynomial function sections & to find with numerical envelope method two envelops of the inscribed circles family of the profile, thus forming...

Introduced in this paper is a new method by which the camber line of the turbine blade profile is described by a number of high order polynomial function sections, and which ensures the absence of flex point that is usually accompnied with that function. The paper offers to give a'description of the radius of the inscribed circles of the profile by a number of high order polynomial function sections & to find with numerical envelope method two envelops of the inscribed circles family of the profile, thus forming the pressure surface and the suction surface of the blade profile respectively.

本文提出了用分段高次多项式来描述涡轮叶型的中弧线,并保证不出现多项式所固有的可能会引起波动危险的一种新方法;提出了用分段高次多项式来描述叶型内切圆的半径;用数值包络法求出叶型内切圆族的两条包络线而构成叶型的叶盆,叶背型面。

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