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nozzle
相关语句
  喷管
    Study on the Unsteady Flow Calculation & Transient Mathematical Model of Vectoring Nozzle
    矢量喷管非定常流场计算与动态数学模型研究
短句来源
    OPTIMUM CONTOUR OF SUPERSONIC EXHAUST NOZZLE
    超音速推力喷管的最佳型线
短句来源
    The Design and Calibration of a Single Jack,Semi-flexible Nozzle Supersonic Intake Wind-tunnel for Mach Number 1.6 to 2.6
    M=1.6~2.6单支点半柔壁喷管的超音速进气道风洞的设计与调试
短句来源
    ANALYTICAL AND EXPERIMENTAL INVESTIGATION OF SUPERSONIC EJECTOR NOZZLE
    超音速引射喷管的分析和实验研究
短句来源
    ONE-DIMENSIONAL TWO-PHASE NOZZLE FLOW
    一维两相喷管流动
短句来源
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  喷口
    Study on Force Loading Servosystem of Jet Nozzle Mechanism
    尾喷口机构的伺服力加载系统研究
短句来源
    Several direct-connect hot tests were done for a variable-area propelling nozzle dual-mode ramjet model combustor on the simulated fly condition of Ma=6 and H=25km.
    在模拟飞行马赫数Ma=6,高度25km的条件下,针对可调喷口液体碳氢燃料双模态冲压模型发动机进行了直连式试验研究.
短句来源
    An Economical Analysis between Pumping with Exhaust Blower and Injecting with Injector to Establish Engine Nozzle Conditions
    抽气机抽气与引射器引气建立发动机喷口环境条件的经济分析
短句来源
    Comprehensive Analysis of Low Pressure Condition Established with Ejection or Compressor Extraction for Afterburner Nozzle
    引射器引气与压气机抽气建立加力燃烧室喷口低压条件的综合分析
短句来源
    Study and Application of Calculation Method for Adjusting the Matching Parameters of Turbine Nozzle Area and Engine Nozzle Radius
    发动机的涡轮导向器面积、喷口直径等匹配参数调整的计算方法研究和应用
短句来源
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  “nozzle”译为未确定词的双语例句
    NUMERICAL SIMULATION OF AXISYMMETRICAL SUPERCRITICAL VISCOUS NOZZLE JET FLOW
    轴对称超临界粘性喷流的数值模拟
短句来源
    MULTIPLE NOZZLE EJECTOR PERFORMANCE CALCULATING MODEL
    多喷嘴引射器性能计算模型
短句来源
    The effective rediation is very strong on the flat and convergent section of the nozzle,but weak on the divergent section.
    壁面有效辐射沿轴向的分布取决于壁温变化,平直段和收敛段有效辐射较强,扩张段有效辐射较弱;
短句来源
    Malfunction analysis to nozzle guide component of turbofan engine
    涡扇发动机涡轮导向器故障分析
短句来源
    Real-time mathematical model for turbofan engine with thrust-vectoring nozzle
    带推力矢量的涡扇发动机实时数学模型研究
短句来源
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  nozzle
For simplicity, the inclination of the nozzle to the wall CE is set equal to 90°.
      
Calculations of axisymmetric jet leaving a nozzle at jet pressure lower than pressure in medium
      
The problem of discharge of a supersonic axisymmetric jet from a nozzle at a jet pressure less than the pressure in the surrounding medium is considered.
      
Calculation of mixed sub- and supersonic gas flow in a plane pressure nozzle
      
For the system of equations of motion of the mixed elliptic-hyperbolic type in the potential plane, a particular solution is found which corresponds to gas motion in a nozzle with a curved sonic line.
      
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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。

Herein given is a description of a newly built single jack, semi-flexible nozzle supersonic intake tunnel, the nozzle exit of which is 160 ×160mm with a range of Mach-number 1.6-2.6 and that of nozzle pitching 15°. This paper gives a brief outline of the design of the air supply system, tunnel facilities, auxiliary systems and the experienca of handling test together with the results obtaied during calibration, The maximum variation of the Mach-numher ΔM/Mcp and the corresponding root mean...

Herein given is a description of a newly built single jack, semi-flexible nozzle supersonic intake tunnel, the nozzle exit of which is 160 ×160mm with a range of Mach-number 1.6-2.6 and that of nozzle pitching 15°. This paper gives a brief outline of the design of the air supply system, tunnel facilities, auxiliary systems and the experienca of handling test together with the results obtaied during calibration, The maximum variation of the Mach-numher ΔM/Mcp and the corresponding root mean square value in the working section are less than ±1.5% and 1% respectively, which are considered to meet the intake test requirements.

本文介绍一个单支点半柔壁喷管的超音速进气道风洞。喷管出口的尺寸是160毫米×160毫米,试验M数范围为1.6~2.6,攻角变化范围为15°(单向)。介绍了供气系统、风洞装置及各系统的设计,还介绍了风洞的调试工作及调试结果。流场校测的结果为:M数偏差(ΔM/M_0)≤±1.5%,M数的均方根偏差小于1%,满足进气道模型试验的要求。

From the view-point of design,this paper mainly represents the new features of a solid propellant rocket engine with several long wires embedded into its grain.The determination of the collocation place of metal wires, the principle of choosing the quantity of wires and the initial grain type and the ratio of initial burning surface to throat area are stated.The local ablation of thermal insulation barrier in nozzle convergence region and of throat insert is analysed.The calculation method for the variation...

From the view-point of design,this paper mainly represents the new features of a solid propellant rocket engine with several long wires embedded into its grain.The determination of the collocation place of metal wires, the principle of choosing the quantity of wires and the initial grain type and the ratio of initial burning surface to throat area are stated.The local ablation of thermal insulation barrier in nozzle convergence region and of throat insert is analysed.The calculation method for the variation of buruning surface during a transition period and the computer program are also introduced.Some experimental curves are plotted in this paper.

本文主要从设计的角度阐述了药柱中加入长金属丝的固体火箭发动机的一些新的特点。论述了金属丝布置位置的确定及金属丝根数的选择原则;初始药型及初始面喉比的选择;分析了喷管收敛段绝热层及喉衬的局部烧蚀问题;阐述了过渡段燃面变化的计算方法,并附有计算机程序。文中附有一些实验曲线。

 
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