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aerodynamic design of
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  气动设计
     SOME PROBLEMS IN THE AERODYNAMIC DESIGN OF ENERGY RECOVERY PARTICULATE GAS TURBINES AND ANALYSIS OF TEST RESULTS
     能量回收烟气透平气动设计的几个问题与试验结果分析
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     Aerodynamic Design of Flying Wing Transport
     飞翼布局运输机气动设计方法研究
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     The optimized aerodynamic design of turbine cascades is presented, which has been based on composite evolutionary algorithms and Navier Stokes equation solution techniques.
     提出了基于复合进化算法和Navier-Stokes方程求解技术的透平叶栅气动设计方法。
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     The Aerodynamic Design of Centrifngal Fans with Low Noise Characteristic
     低噪声性能离心风机的气动设计
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     The results show that increase of flow Reynolds number and decrease of sensitivity of turbine performance to Reynolds number are two key technologies to aerodynamic design of high performance LPT.
     设计结果表明提高涡轮工作雷诺数和降低涡轮性能对雷诺数变化的敏感程度是低雷诺数环境下高性能涡轮气动设计的关键。
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  “aerodynamic design of”译为未确定词的双语例句
     Optimum Aerodynamic Design of Transonic Wing Based on Viscous Adjoint Method
     基于黏性伴随方法的跨声速机翼气动优化设计
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     Optimized Aerodynamic Design of Turbine Cascades Based on Composite Evolutionary Algorithms and Navier-Stokes Equation Solution Techniques
     基于复合进化算法和Navier-Stokes方程求解技术的透平叶栅气动优化设计
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     Optimum Method and Inverse Method for Aerodynamic Design of Airfoil
     翼型的气动最优化设计方法和反设计方法
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     An Optimal Control Method for Aerodynamic Design of Airfoil with Multi-Constraint Conditions
     气动/几何约束条件下翼型优化设计的最优控制理论方法
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     Based on the optimal control theory and Navier-Stokes equations,aerodynamic design of airfoil with multi-constraint conditions,such as aerodynamic and geometric constraint conditions,is studied.
     基于最优控制理论原理和Navier-Stokes方程,研究了气动/几何约束条件下多设计变量的翼型气动优化设计问题.
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  相似匹配句对
     AERODYNAMIC DESIGN PROBLEMS OF PROPFAN
     桨扇气动设计问题
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     ’s design.
     的设计,平均性能提高26%。
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     In design, .
     设计过程中应用了.
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     Aerodynamic Design Technology for the Trike
     动力三角翼飞行器气动力设计技术
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     THE AERODYNAMIC DESIGN FOR AEROSPACE PLANE
     空天飞机的气动设计
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  aerodynamic design of
Method of Optimization of Blade Shapes in Aerodynamic Design of the Fan Cascade
      
Many problems arising in the aerodynamic design of aerospace vehicles require the numerical solution of the Euler equations of gas dynamics.
      
Aerodynamic design of airfoils based on variable-domain variational finite element method
      
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.
      
The aerodynamic design of flow devices is one of the most important process in the quest for high efficiency in the turbo-machinery industry.
      
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Aerodynamic design of a transonic axial-flow compressor for research purpose has been completed based on Wu's three-dimensional flow theory in turbomachines. Through 5 cycles of iteration between inverse calculations on a single mean S2 stream surface and direct calculations on a family of S1 surfaces of revolution, final convergent solution of the three-dimensional flow is reached. It implies that the coincidence of corresponding streamlines on the two kinds of stream surfaces and approximate equality...

Aerodynamic design of a transonic axial-flow compressor for research purpose has been completed based on Wu's three-dimensional flow theory in turbomachines. Through 5 cycles of iteration between inverse calculations on a single mean S2 stream surface and direct calculations on a family of S1 surfaces of revolution, final convergent solution of the three-dimensional flow is reached. It implies that the coincidence of corresponding streamlines on the two kinds of stream surfaces and approximate equality of parameters on them, such as Vθγ, △s/R and thickness of the stream surfaces. At the same time, the flow passage and the blade airfoil meeting all design criteria are determined. The flow field analysis of supersonic sections has shown that parameters such as Vor, As/R etc. all undergo a sudden jump through the shock.

基于吴仲华的三元流动理论,完成了单级跨声速轴流式研究压气机的气动热力学设计.经过两类流面的五轮迭代计算,S_1迥转面上的中心流线与中心S_2流面上相应流线的形状基本重合,其上参数如V_(θr)、△_s/R和流片厚度等大致相等,获得了三元流场的收敛解,同时也确定了满足各项设计判断准则及所需流量的流道和叶型.对超声速进气截面的流场分析表明,由于通道激波的滞止作用,波后的V_(θr)、△_s/R等量都发生了突跃.

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。

 
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