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翼型     
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  airfoil
     The experimental results indicate that for highness of Gurney flap 0.010c,the maximum statical and dynamical lift coefficient of OA212MK rotor airfoil increases 22% and 16%,the maximum statical and dynamical lift coefficient of OA212MK+TAB increases 19% and 5%,respectively. 
     实验结果表明,高度为0.010c的Gurney襟翼使OA212MK旋翼翼型的最大静态和动态升力系数分别增加了22%和16%,而使OA212MK+TAB的最大静态和动态升力系数分别增加了19%和5%。
短句来源
     Detached-Eddy Simulation for Airfoil Stall
     Detached Eddy Simulation方法模拟不同类型翼型的失速特性
短句来源
     Aerodynamic optimization design of transonic airfoil and wing based on Navier-Stokes equations
     基于Navier-Stokes方程跨声速翼型和机翼气动优化设计
短句来源
     This paper describes the design and calculation of an airfoil cooling fan in B6135Q 2 diesel engine for SH163 15 Ton truck.
     本文介绍了SH 163型15吨载货汽车配用的B 6135Q 21机翼型风扇的设计与计算。
短句来源
     THE TRANSONIC WIND TUNNEL TEST RESEARCH FOR THE SUPERCRITICAL NATURAL LAMINAR AIRFOIL NPU-L72513
     超临界自然层流翼型NPU-L72513的风洞试验研究
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  airfoils
     Numerical Optimization Design for Transonic Airfoils
     应用伴随方程的跨声速翼型数值优化设计
     As application, hybrid genetic algorithm is used to carry out inverse design and wave optimization design of transonic airfoils.
     应用混合遗传算法进行跨音速翼型的反设计和波阻优化设计,并与采用优选策略的标准遗传算法的设计结果进行比较。
短句来源
     Two reversible airfoils R 18 and R43T have been selected.
     在此基础上,优选出两个可逆翼型-R18和R43T。
短句来源
     AERODYNAMIC ANALYSIS AND MODIFICATION DESIGN OF NPU AIRFOILS
     NPU翼型的气动力分析和改进设计
短句来源
     We present a numerical investigation of flutter characteristics of three supercritical airfoils (RAE2822, DFVLR-R2, NPU-3) with two degrees of freedom--bending/torsion--in transonic flow.
     研究了结构参数完全相同的 3个超临界翼型( RAE2 82 2 ,DFVLR- R2和 NPU- 3)的跨声速颤振特性。
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  aerofoil
     The aerofoil of blade adopt NACA63-412, the blade tip is half a circle, chords are decrease from 190mm at 110mm of the rotor center to 107mm at the rotor tip and setting angles accordingly decrease from 19°to 0°.
     该叶片翼型采用 NACA63-412,叶尖形状为半圆形,叶片弦长从距叶轮中心 110mm 处 190mm 向尖部 107mm 递减,其安装角也相应的从 19°向尖部 0°递减。
短句来源
     Based on investigating air-dynamics characteristics of blade with different aerofoils, NACA6321, NACA23015 and NACA4412 are chosen as the turbine blade aerofoil of NACAZ1, NACAZ2 and NACAZ3 respectively, which are used for experimental turbine blades in PPSS.
     在对比了不同翼型的气动性能之后,优选出具有NACA6321、NACA23015和NACA4412三种翼型的叶片NACAZ1、NACAZ2和NACAZ3作为吊舱发电系统实验用涡轮叶片。
短句来源
     Study of Automatic Checking Device for Grinding Inner - circle of Aerofoil bearing of M2110A Grinder
     M2110A磨床翼型轴承座磨内圆自动检测装置研究
短句来源
     Jameson/TVD Schemes Applied to Simulating the Flow around Rotor Aerofoil
     Jameson/TVD格式应用旋翼翼型绕流分析
短句来源
     Analysis of Grinding Crack for Aerofoil Bearing Bracket Made of 20CrMnTi Steel
     20CrMnTi钢翼型轴承座磨削裂纹的分析
短句来源
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  an airfoil
     This paper describes the design and calculation of an airfoil cooling fan in B6135Q 2 diesel engine for SH163 15 Ton truck.
     本文介绍了SH 163型15吨载货汽车配用的B 6135Q 21机翼型风扇的设计与计算。
短句来源
     Supersonic Flutter Analysis of an Airfoil with Cubic Structural Nonlinearity
     超音速结构非线性翼型的颤振分析
短句来源
     The experimental results indicate that the effect of Gurney flap in increasing the lift is closely related with the height of the flap. Gurney flap can increase the lift coefficient of an airfoil to 53%, when α =8° and height=3% c.
     研究结果表明 ,Gurney襟翼的增升效果与其高度密切相关 ,在α =8°时 ,高度为 3%弦长的Gurney襟翼使翼型的升力系数增加了 5 3% .
短句来源
     Design and Calculation of an Airfoil Cooling Fan
     机翼型冷却风扇的设计与计算
短句来源
     Simulation of Flow Around an Airfoil by the Lattice Boltzmann Method
     基于Lattice Boltzmann方法的翼型绕流数值模拟
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  airfoil
The unsteady effects in upstream airfoil rows are weaker than those in downstream airfoil rows in the VCRT.
      
A large number of papers have been devoted to the study of unsteady flow past airfoil cascades.
      
Experimental investigation of the distribution of the pressure on a triangular airfoil with blunt edges at small angles of attac
      
The article gives the results of an experimental investigation of the pressure on a triangular airfoil with blunt edges with a half aperture angle ?=45° under angles of attack α=0,5,10°, with M∞=11.6 and Re≈1.5×106.
      
Hypersonic flow past an airfoil with a mach system of shock waves
      
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  airfoils
Aerodynamic interference of airfoils in a subsonic unsteady flow
      
Integral equations [1] are used to study the case of unsteady gas flow about a system consisting of a finite number of airfoils.
      
As an example, the aerodynamic forces acting on the airfoils of a biplane in an unsteady subsonic gas flow are calculated.
      
Design of airfoils stall-free on a given range of angles of attack
      
A cylinder was chosen for the present study because it is a classical body, and the results obtained in investigations of it can, in a certain sense, be extrapolated to other bodies, for example, airfoils.
      
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  aerofoil
Laminar boundary layer in a flow past an aerofoil with a circular cavity
      
The paper describes a numerical study of a method of preventing the separation of a laminar boundary layer from the forward section of a symmetric aerofoil, the flow past which does not separate at zero angle of incidence.
      
In order to increase the maximum angle of incidence at which the flow has still not separated, a circular cavity (vortex cell) located almost completely inside the aerofoil is introduced on the segment vulnerable to separation.
      
A study of 3D aerodynamic design for a transonic compressor blading optimized by the locations of aerofoil maximum thickness and
      
An aerofoil above which is built the artificial cavity low pressure region is called "cavitating airfoil".
      
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  an airfoil
Hypersonic flow past an airfoil with a mach system of shock waves
      
Calculation of intense blowing on a blunt body and an airfoil
      
Transonic flows around an airfoil in wind tunnels with porous walls
      
A study is made of two-dimensional transonic flows of gas around an airfoil in the working part of a wind tunnel with porous walls.
      
The various approximate approaches to the investigation of the unsteady aerodynamic characteristics of an airfoil with jet flap [1-3] are applicable only for an airfoil, low jet intensity, and low oscillation frequencies.
      
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