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喷管设计
相关语句
  nozzle design
     Nozzle Design and Numerical Simulation Method of Nozzle Flow in DF/HF Chemical Lasers
     DF/HF化学激光器喷管设计和数值模拟
短句来源
     Supersonic Annular Nozzle Design
     超音速环状喷管设计
短句来源
     This method can be extended to unsteady transonic nozzle flow calculations and used for nozzle design of engineering application
     计算结果与实验结果以及其他计算结果符合良好,此法可推广到非定常跨音速喷管流动的计算,并可用于工程中喷管设计
短句来源
     Three-dimensional nozzle design
     三维喷管设计
短句来源
     Based on the aerodynamic window's principle and aerodynamic theory,a method of nozzle design is presented. The factors influencing the mass ratio are obtained. The design of aerodynamic window is studied,and the curves of nozzle are obtained.
     根据超声速自由旋涡气动窗口的实现原理以及相关气动设计理论,推导出气动窗口的质量流率公式,得到影响气动窗口质量流率的几个因素,研究了自由旋涡气动窗口喷管设计过程,利用特征线方法设计非对称喷管,得到气动窗口的喷管型面。
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  “喷管设计”译为未确定词的双语例句
     Research on Design of Nozzle in Scramjet
     超燃冲压发动机尾喷管设计方法研究
短句来源
     Nozzle afterbody design of hypersonic flight vehicle
     高超声速飞行器后体喷管设计
短句来源
     Experiments and CFD simulationshowed that the small signal gain was larger than 1×10~(-2) cm~(-1).
     这一独特的喷管设计适于以氮气为载气的COIL,三维数值模拟与实验结果表明,光腔流场的小信号增益系数大于1×10~(-2) cm~(-1)。
短句来源
     These results may be helpful to design and manufacture an appropriate nozzle of the jet O 2(1Δ) generators for COIL.
     这些结果对化学氧碘激光的射流式 O2 ( 1Δ)发生器的喷管设计和制造提供了有价值的参考。
短句来源
     One is based on a design method fothe maximum thrust nozzle of Rao.
     一种是基于 Rao 的最大推力喷管设计方法;
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  相似匹配句对
     Three-dimensional nozzle design
     三维喷管设计
短句来源
     THE AERODYNAMIC DESIGN OF NOZZLE FOR AEROSPACE PLANE
     空天飞机喷管的气动设计
短句来源
     To design the G.
     在设计G.
短句来源
     Design
     设计
短句来源
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  nozzle design
Supersonic nozzle design with allowance for viscosity
      
On the choice of approximations in direct problems of nozzle design
      
The investigation results (the optimal spray parameters) were used to guide the water nozzle design.
      
The micro-nozzle design and optimization is mathematically provided.
      
The side-load character strongly depends on the nozzle design, and is a key feature for the nozzle's mechanical structure layout.
      
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Transonic flow in the throat region of hyperbolic Laval nozzles is analysed using the conformal curvilinear coordinate method. A solution to this type flow is given for the cases of different radii of wall curvature at the throat and different values of the ratio of the specific heats. The general behaviour of the transonic flow and Mach number distribution in the throat region are presented. This method gives fine accuracy. It can be applied in the designing of nozzles, especially, in the designing of aerodynamic...

Transonic flow in the throat region of hyperbolic Laval nozzles is analysed using the conformal curvilinear coordinate method. A solution to this type flow is given for the cases of different radii of wall curvature at the throat and different values of the ratio of the specific heats. The general behaviour of the transonic flow and Mach number distribution in the throat region are presented. This method gives fine accuracy. It can be applied in the designing of nozzles, especially, in the designing of aerodynamic laser nozzles.

本文采用保角曲线坐标方法分析双曲型喷管喉部跨声速流动特性,给出了跨声速双曲型喷管流动的一般解.这个解适用于不同的喉部壁面曲率半径,适用于不同的比热比.通过计算给出了不同比热比下喉部跨声速流场的主要参数与曲率半径的关系以及典型跨声速流场的等马赫数线分布.本方法计算简单,精度较高,可作喷管设计,特别是气动激光喷管设计参考.

Based on practical work in 1971~1976, some problems to be considered in designing of rapid expansion nozzles for gas-dynamic lasers were summarized, including the selection of important parameters,, the discussion on methods for contoured nozzles design and the correction for boundary layer grouth etc. Through a large amount of numerical analysis, a simple convenient method for correcting boundary layer grouth under various conditions was also presented.

在过去实际工作的基础上(1971~1976),总结了气动激光器快速膨胀喷管设计时应考虑的一些问题,包括主要参数的选择、喷管理论型壁的计算和边界层修正方法的讨论等.同时,通过大量的计算分析,给出了不同条件下边界层修正的简便方法.在过去实际工作的基础上(1971~1976),总结了气动激光器快速膨胀喷管设计时应考虑的一些问题,包括主要参数的选择、喷管理论型壁的计算和边界层修正方法的讨论等.同时,通过大量的计算分析,给出了不同条件下边界层修正的简便方法.

By means of the Pontryagin Maximum Principle, an optimization analysis is presented for nozzles with one-dimensional two-phase flows. Choosing the slope of the contour as a control variable, we verified that the optimal nozzle surface was a conical surface composed of straight lines. Furthermore we discussed the method of defining the optimal contour in the supersonic and subsonic regions.This paper may be the theoretical base of the design of nozzle and the computation reference.

本文利用Pontryagin极大值原理,研究了一元两相流动最佳喷管型面问题。利用斜率作为控制变量,论证了最佳型面是斜率为常数的直线族所组成的锥面。并讨论了亚音速段和超音速段最佳轮廓线的确定方法。本文可为喷管设计提供理论依据和计算参考。

 
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