助手标题  
全文文献 工具书 数字 学术定义 翻译助手 学术趋势 更多
查询帮助
意见反馈
   型风洞 的翻译结果: 查询用时:0.233秒
图标索引 在分类学科中查询
所有学科
更多类别查询

图标索引 历史查询
 

型风洞
相关语句
  model wind tunnel
     The development of half-model subsystem in DCS control system on some model wind tunnel
     某型风洞DCS控制系统半模子系统的研制
短句来源
     The design of adjusting-press subsystem in DCS gather-scatter system on some model wind tunnel
     某型风洞DCS系统调压子系统的设计
短句来源
     This paper puts the program of normal half-model control and that of location check inside the PLC-200 in pitching angle control to the experiment model,with EM277 communication module,it is connected with the PROFIBUS cable of some model wind tunnel and becomes a subsystem in DCS gather-scatter control system on some model wind tunnel,then it is fulfilled that IPC further control and manage the half-model subsystem.
     在对实验模型的攻角控制中,使用可编程控制器PLC-200将常规半模控制与位置检测程序内置其中,通过EM277通讯模块,将该系统上挂于某型风洞PROFIBUS总线,使其升级为某型风洞DCS集散控制系统中的一个子系统,实现了某型风洞DCS系统中主控算机IPC对半模机构的远程控制与管理。
短句来源
  “型风洞”译为未确定词的双语例句
     On the basis of the FBY-1 type examination meter of the wind-gauge in the wind channel,this article introduces the elementary constitute,the software design and the effective measures which is adopted for practical problem.
     本文是在笔者最近研制的FBY-1型风洞风表检定仪8031系统的基础上整理而成的,主要介绍了这个简单而实用系统的基本组成、软件设计以及针对现场实际问题所采用的有效措施
短句来源
     FREE FLIGHT METHOD IN HYPESONIC IMPULSE TYPE TUNNELS FOR STATIC AND DYNAMIC STABILITY STUDY
     在高超声速脉冲型风洞中测量静、动稳定性导数的模型自由飞方法
短句来源
     THE ACCELEROMETER FORCE BALANCE USED IN THE IMPULSE WIND TUNNEL
     脉冲型风洞用加速度计测力天平
短句来源
     Among tunnels of similar types in the country,the NH-1 is first fitted with variable porosity walls to calibrate the flow quality of M=1.35 contoured nozzle blocks. The result is satisfactory and the transonic test Mach number range is extended from 0.6-1.2 to 0.6-1.42.This paper also presents the expression of calibration parameter ΔM thus improving the accuracy of freestream Mach number.
     在国内AT—1型风洞中,我们首次使用变开孔壁板,调试了M=1.35二元型面喷管,获得了较满意的结果,从而扩大了NH—上风洞跨音速试验范围,实验M数从原来的0.6~1.2改进为0.6~1.42。 文中还结出了风洞校测参数ΔM的修正公式,从而提高了实验M数的准确性。
短句来源
     This paper describes the principle of the accelerometer force balance. It can measure aerodynamic forces and moments at a short period of test time(less than 3 ms).
     在工作时间<3ms的脉冲型风洞中的试验模型上选定位置处,安装加速度计来进行力和力短的测量。
短句来源
更多       
  相似匹配句对
     (2)C shape;
     C ;
短句来源
     (3)D shape.
     D
短句来源
     Wind Tunnel Experiment on the Aerodynamic Performances of H-shaped Booms
     H截面吊杆气动性能的风洞试验
短句来源
     THE ACCELEROMETER FORCE BALANCE USED IN THE IMPULSE WIND TUNNEL
     脉冲风洞用加速度计测力天平
短句来源
     THE WIND TUNNEL TESTING FOR AERO-SPACE PLANE
     空天飞机的风洞试验
短句来源
查询“型风洞”译词为用户自定义的双语例句

    我想查看译文中含有:的双语例句
例句
为了更好的帮助您理解掌握查询词或其译词在地道英语中的实际用法,我们为您准备了出自英文原文的大量英语例句,供您参考。
  model wind tunnel
Sectional versus full model wind tunnel testing of bridge road decks
      
An element of that work is scale-model wind tunnel tests of the airframe to predict flight performance.
      


The Northwestern Polytechnical University 10 by 30 cm. transonic airfoil wind tunnel was converted from the 30 by 30 cm. supersonic wind tunnel in 1976. This facility is a two-dimensional tunnel with parallel sidewalls and top and bottom slotted walls which operates on direct blowdown from a supply of dry air. On each sidewall, there is a turnable disk at the region occupied by the model. Various open-area-ratios may be obtained by sealing some slots of the slotted walls. The tunnel is capable of operating at...

The Northwestern Polytechnical University 10 by 30 cm. transonic airfoil wind tunnel was converted from the 30 by 30 cm. supersonic wind tunnel in 1976. This facility is a two-dimensional tunnel with parallel sidewalls and top and bottom slotted walls which operates on direct blowdown from a supply of dry air. On each sidewall, there is a turnable disk at the region occupied by the model. Various open-area-ratios may be obtained by sealing some slots of the slotted walls. The tunnel is capable of operating at Mach number from 0.4 to 1.0 with corresponding Reynolds number range of 3×106 to 6×106 based on a 10 cm chord. Empty tunnel calibrations show that the local Mach number distribution obtained from wall static pressure varies less than ±0.005 from the average value in the test region occupied by the model.Surface pressure distributions on three RAE-104 section models with 5 cm., 10 cm. and 12.5 cm. chords respectively were measured in conditions of zero angle of attack: the Mach number range of about 0.4 to 0.8 and several open-area-ratios. Results of measurements show that when the value of open-area-ratio is 0.02 and the corresponding wind tunnel parameter T equals 0.64, the blockage interference practically vanishes.Comparisons between surface pressure distributions of RAE-104 section models which were obtained under three conditions of sidewalls show that;1.The lift coefficients obtained under conditions of porous turnable disk without local sidewall suction are much less than those obtained under conditions of free interference.2.The lift coefficients obtained under conditions of the solid turnable disk closely approach those under conditions of free interference, when the Mach number is less than 0.7.3.It is found that under the conditions of larger Mach numbers and angles of attack the turnable disk with local sidewall suction is the best one in the three.The comparison between results in this facility and those in the British National Physical Laboratory 20 by 8 inch transonic tunnel is presented.

在西北工业大学跨音速翼型风洞(又名57风洞)中,对弦长分别为50、100、125毫米的三个RAE 104翼型模型进行了压力分布测量。结果表明:当上下壁开闭比选用2%时,风洞的堵塞干扰基本消除。 采用实侧壁、多层网板而不进行抽气及多层网板进行抽气这三种侧壁状态,对RAE 104翼型模型所做实验结果表明:有多层网板而不抽气,使升力系数大大低于无干扰值;在M

The determination of optimum parameters of variable porosity wall is one of the important subjects in wind tunnel design optimization.Therefore,the NH-1 wind tunnel transonic variable porosity walls test section has been calibrated and adjusted successively.The result indicates that the improved transonic flow quality attains the advanced domestic level.Among tunnels of similar types in the country,the NH-1 is first fitted with variable porosity walls to calibrate the flow quality of M=1.35 contoured nozzle...

The determination of optimum parameters of variable porosity wall is one of the important subjects in wind tunnel design optimization.Therefore,the NH-1 wind tunnel transonic variable porosity walls test section has been calibrated and adjusted successively.The result indicates that the improved transonic flow quality attains the advanced domestic level.Among tunnels of similar types in the country,the NH-1 is first fitted with variable porosity walls to calibrate the flow quality of M=1.35 contoured nozzle blocks.The result is satisfactory and the transonic test Mach number range is extended from 0.6-1.2 to 0.6-1.42.This paper also presents the expression of calibration parameter ΔM thus improving the accuracy of freestream Mach number.

如何选择变开孔壁板的最佳参数是风洞优化设计的重要课题之一。为此,我们对NH—1风洞跨音速变开孔壁继续进行了综合参数调试的实验研究,结果表明,改善了跨音速流场品质,达到了国内较先进水平。 在国内AT—1型风洞中,我们首次使用变开孔壁板,调试了M=1.35二元型面喷管,获得了较满意的结果,从而扩大了NH—上风洞跨音速试验范围,实验M数从原来的0.6~1.2改进为0.6~1.42。文中还结出了风洞校测参数ΔM的修正公式,从而提高了实验M数的准确性。

Experimental data of an airfoil wind tunnel are much influenced by upper-lower- and side-wall interferences. Although the upper and lower walls areventilated through longitudinal slots or small holes, wind tunnel interferenceconstitutes a serious problem for models tested in the transonic regime. Oneway to avoid wall interference is to build large test section wind tunnel or touse small models. However, large test sections require expensive tunnels andsmall models usually make Reynolds number too low. Hence...

Experimental data of an airfoil wind tunnel are much influenced by upper-lower- and side-wall interferences. Although the upper and lower walls areventilated through longitudinal slots or small holes, wind tunnel interferenceconstitutes a serious problem for models tested in the transonic regime. Oneway to avoid wall interference is to build large test section wind tunnel or touse small models. However, large test sections require expensive tunnels andsmall models usually make Reynolds number too low. Hence it is necessary tostudy experimentally the effect of the ratio of the half height of the test sec-tion (S) to the airfoil chord (L) on the flow around airfoils. An experimental investigation has been conducted in the Transonic WindTunnel of the Institute of Aerodynamics and Gasdynamics (IAG) of StuttgartUniversity to determine the effects of the ratio S/L. It is hoped that thepermissible value of S/L for different ranges of Mach number can be ascer-tained through experiments, so that the airfoil model chord and also the Machnumber can be justifiably increased. This investigation indicates that, whenMach number is smaller than 0.75, the ratio S/L can be reduced to 1.25 withoutintroducing siginificant effects of model blockage interference. But for theexperiments involving angle of attack and with S/L<1.5 we can not obtainsatisfactory results for the lift coefficient. In order to ascertain the effects of the side wall interference at the testsection, an experimental investigation in IAG Transonic Airfoil Wind Tunnelhas been conducted to study the two-dimensionality of the flow around airfoils.The experimental results indicate that the two-dimensionality of the stream isinfluenced not only by Mach number of the stream and model angle of attackbut also seriously by the value of the ratio S/L. The experimental data of thetwo-dimensionality research show that when the angle of attack is 6°or 8°, the two-dimensionality of the stream around the model for S/L=1.5 is muchworse than those for S/L=2.0. Hence for small S/L and large angle of attack,comparable to those mentioned above, careful consideration should be given toside wall boundary layer control technique.

西德斯图加特大学空气动力学与气体动力学研究所(IAG)的跨音速翼型风洞的实验M数范围为0.4~0.95,采用喉道面积控制法,M数最大误差不超过±0.0035。该风洞有性能较好的三分力天平。模型在风洞中不对称放置,以减小上壁面对翼型上表面的压力分布的干扰,即可增大翼型弦长(L)与风洞半高(S)之比,从而可增大实验雷诺数。在该风洞中对于风洞半高及翼型弦长之比(S/L)对升力系数及流动二元性的影响进行了实验研究,结果表明,当M<0.70时,S/L可以小至1.25.其堵塞干扰仍没有明显的影响,但做有迎角的实验时,当S/L<1.5时,升力系数曲线得不到满意的结果。本文也给出了不同S/L值时流动二元性随M数及迎角的变化情况,由实验结果可以看出,流动二元性不仅随M数及迎角有较大的变化,而且受S/L的影响。

 
<< 更多相关文摘    
图标索引 相关查询

 


 
CNKI小工具
在英文学术搜索中查有关型风洞的内容
在知识搜索中查有关型风洞的内容
在数字搜索中查有关型风洞的内容
在概念知识元中查有关型风洞的内容
在学术趋势中查有关型风洞的内容
 
 

CNKI主页设CNKI翻译助手为主页 | 收藏CNKI翻译助手 | 广告服务 | 英文学术搜索
版权图标  2008 CNKI-中国知网
京ICP证040431号 互联网出版许可证 新出网证(京)字008号
北京市公安局海淀分局 备案号:110 1081725
版权图标 2008中国知网(cnki) 中国学术期刊(光盘版)电子杂志社