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   气动设计 在 航空航天科学与工程 分类中 的翻译结果: 查询用时:0.061秒
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  aerodynamic design
Aerodynamic design by jointly applying S2 flow surface calculation and modern optimization methods on multistage axial turbine
      
A study of 3D aerodynamic design for a transonic compressor blading optimized by the locations of aerofoil maximum thickness and
      
The blade row interaction can alter the time-mean flow and therefore be of interest for aerodynamic design analysis.
      
Study on aerodynamic design optimization of turbomachinery blades
      
Blade parameterization and aerodynamic design optimization for a 3D transonic compressor rotor
      
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  aerodynamics design
This paper describes the study on aerodynamics design optimization of turbomachinery blading developed by the authors at the Institute of Engineering Thermophysics, Chinese Academy of Sciences, during the recent few years.
      
Taken the developing of the above proposed algorithm as a beginning step, our long range research object is the aerodynamics design.
      
The aerodynamics design can be studied using the optimal control theory.
      
  aerodynamic design of
The present paper describes an optimization methodology for aerodynamic design of turbomachinery combined with a rapid 3D blade and grid generator (RAPID3DGRID), a N.S.
      
Aerodynamic design of airfoils based on variable-domain variational finite element method
      
Many problems arising in the aerodynamic design of aerospace vehicles require the numerical solution of the Euler equations of gas dynamics.
      
Method of Optimization of Blade Shapes in Aerodynamic Design of the Fan Cascade
      
Aerodynamic design of fans, blowers and pumps have significantly improved the performance over the operating range.
      
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A general program using finite-difference method is written to calculate the flow field of supersonic axisymmetric nose inlet. This program is suitable to the direct problem of aerodynamic design of inlets e. g. pitot-type, single-cone, bicone, triple-cone and isentropic cone etc. Since "seperation singularity" difference method and implicit-explicit difference scheme are adopted in the calculation of inviscid flow field in the inlet, results of calculation are obtained with second order accuracy at boundary...

A general program using finite-difference method is written to calculate the flow field of supersonic axisymmetric nose inlet. This program is suitable to the direct problem of aerodynamic design of inlets e. g. pitot-type, single-cone, bicone, triple-cone and isentropic cone etc. Since "seperation singularity" difference method and implicit-explicit difference scheme are adopted in the calculation of inviscid flow field in the inlet, results of calculation are obtained with second order accuracy at boundary points and internal points, as well as near singular points. This program can offer required internal and external flow characteristics of inlets.Numerical results for five examples are in satisfactory agreement with corresponding results obtained from the method of characteristics and experimental data.

为了计算超音速轴对称头部进气道的流场,采用有限差分法编制了一个通用计算程序。该程序适用于皮托式、单锥、双锥、三锥、等熵锥等各种进气道的正问题气动设计。由于在进气道无粘流场计算中,采用了分离奇性的差分方法及混合使用显、隐差分格式,所以在边界点和内点及奇点邻域,计算结果均达到二级精度。程序可瑜出所需要的进气道各内流特性及外流特性。 文中列生了五个计算实例,并与特征线法计算结果和实验结果作了比较。符合程度令人满意。

The present paper gives a new solution method of 2-D cascade flow, in which the free streamline boundary conditions can be satisfied. This is a cross-iterative calculation method between two correlating flow fields. The 2-D subsonic flow problem for calculating the upstream and downstream regions of the ordinary blade cascade, the splitter and the tandem blade cascades is discussed from an unified viewpoint. The computer program can be available for these three cases.For calculating the splitter and the tandem...

The present paper gives a new solution method of 2-D cascade flow, in which the free streamline boundary conditions can be satisfied. This is a cross-iterative calculation method between two correlating flow fields. The 2-D subsonic flow problem for calculating the upstream and downstream regions of the ordinary blade cascade, the splitter and the tandem blade cascades is discussed from an unified viewpoint. The computer program can be available for these three cases.For calculating the splitter and the tandem blade cascades a physical condition of minimum disturbance of the flow field is proposed, so that the flow division of the two blade channels formed by the splitter blade or the splitter stream surface can be calculated.Some results of numerical examples are presented and compared with the experimental data, the comparison has proved preliminarily the validity of both the presented method and the proposed physical condition for determining the flow division. Some useful thoughts are also given concerning the aerodynamic design of the splitter blade rotors.

本文提出一种满足自由流线边界条件二元叶栅的新解法——两个相关流场交叉迭代的计算方法,统一地论述了普通叶栅的上下游区、分流叶片叶栅和串列叶栅的二元亚音速流场计算问题,计算程序可以通用于这三种情况。 在分流叶片叶栅和串列叶栅的计算中提出了一种流场最小干扰的物理条件,从而可以计算出由分流叶片或分流面所形成的两个叶道之间的流量分配比。 介绍了数值计算结果,并与试验数据作了比较,这些计算与比较初步验证了本文方法,以及所建议的计算流量分配比物理条件的合理性,并对分流叶片叶轮的气动设计提出了一些有益的设想。

The accelerating airflow Problem in the transonic test section with perforated wall is investigated from three aspects:(1)The axial distribution of open-area ratio;(2)The determination of design parameters of the accelerating section;(3)The design of the local disturbance region.A forumla is deduced for calculating the porosity distribution of the accelerating section,thus a further improvement is made of the design of accelerating section.In consideration of tne well-known law of forbidden signals in supersonic...

The accelerating airflow Problem in the transonic test section with perforated wall is investigated from three aspects:(1)The axial distribution of open-area ratio;(2)The determination of design parameters of the accelerating section;(3)The design of the local disturbance region.A forumla is deduced for calculating the porosity distribution of the accelerating section,thus a further improvement is made of the design of accelerating section.In consideration of tne well-known law of forbidden signals in supersonic flow,the local disturbance region design is made for obviating overexpansion of airflow.This is a new concept in the art of designing ventilating wall.

本文从三个方面研究了跨音速风洞实验段中气流的加速问题 1.加速段开闭比的分布规律; 2.加速段设计参数的确定; 3.影响区设计。 本文从喷管曲线的气动设计着眼,推出了加速段开闭比分布的计算公式,从而进一步解决加速段的设计问题。最后从著名的禁讯法则出发,提出和克服过膨胀现象有关的影响区设计问题,这是通气壁设计时要注意的新概念。

 
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