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   complete aircraft 的翻译结果: 查询用时:0.026秒
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complete aircraft
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  全机
     A Numerical Solution for the Complete Aircraft's Subsonic-Transonic-Supersonic Flow at Angles of Attack from 0°to 60°
     迎角从0°到60°全机亚跨超音速绕流数值解法
短句来源
     THE CALCULATION METHOD FOR SUBSONIC LONGITUDINAL AND LATERAL AERODYNAMIC CHARACTERISTICS OF COMPLETE AIRCRAFT CONFIGURATION
     亚声速全机纵横向气动特性计算方法
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     The results of calculation are in good agreement with experimental data of wing surface pressure distributions and aerodynamic characteristic for complete aircraft.
     计算的机翼压力分布及全机气动力系数与实验值符合良好。 表明了本文所采用的计算网格生成技术及流场计算方法是有效、可行的。
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     An Investigation on the Boundary Layer Flow State of Complete Aircraft Model by Using Infrared Imaging Technique
     全机模型附面层状态红外热像探测研究
短句来源
     Euler equations are solved in the generated grid of the twin tail fighter and the computed results of the aerodynamic coefficients of the complete aircraft, the wing surface pressure and the vortical flow field are reasonable.
     在所生成的双立尾战斗机分块结构网格中分区求解Euler方程,获得了合理的全机气动力系数、翼面压力分布和绕流图谱结果
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  “complete aircraft”译为未确定词的双语例句
     THE INTERFERENCE EFFECTS OF SUPPORT SYSTEM OF AIRFOIL SECTION VENTRAL STRUT AND STING ON COMPLETE AIRCRAFT MODEL WITH LARGE ASPECT RATIO AND ITS COMPONENTS
     翼型叶片腹支/尾支对大飞机全机及部件的干扰──大飞机全模试验技术及支撑干扰研究之三
短句来源
     NUMERICAL CALCULATION OF INTERACTION OF PROPELLER SLIPSTREAM ON FLOWFIELD OVER A COMPLETE AIRCRAFT
     螺桨滑流对全机绕流干扰的数值计算
短句来源
     NUMERICAL SOLUTION OF THE EULER EQUATIONS FOR THE TRANSONIC FLOW ABOUT THE COMPLETE AIRCRAFT AT HIGH ANGLES OF ATTACKE
     跨音速大迎角绕流的Euler方程数值模拟
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     A Method of Generating BodyFitted and BodyNormalGrid for a Complete Aircraft
     一种生成全机实用复杂外形计算网格的抛物型方程方法
短句来源
     Numerical Solution of the Euler Equations for the Transonic Flow about the Complete Aircraft at High Angles of Attack
     全机跨音速大迎角绕流的数值分析
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  相似匹配句对
     complete system.
     完备的体系结构。
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     the complete period;
     定型期;
短句来源
     Improvement of Aircraft Direct Lift Control through Complete Decoupling
     用完全解耦改善直接升力控制
短句来源
     A complete solution of aircraft acoustic localizationis obtained by the thesis.
     本文所研究的关键技术,可构成飞行器声被动定位系统一个完整的解决方案。
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     B.W. to the aircraft performances.
     电传飞控 /主动控制对飞机性能的影响。
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  complete aircraft
Thus, the parallel multiblock full Navier-Stokes code can be successfully used for large-scale practical aerodynamic simulations of a complete aircraft on millions-points grids on a daily basis, as needed in industry.
      
Combinations of such streamsurfaces may be built up piecemeal into complete aircraft configurations, and it is shown that the method is sufficiently flexible to allow considerable freedom of choice in the disposition of lift and volume.
      
We are committed to supporting the complete aircraft life cycle from initial concept to aging aircraft retrofits.
      
The complete aircraft was modelled using a few modes of vibration, including rigid-body modes.
      
The KC-135 priming operation was limited to the leading edges, while the B-52 was a complete aircraft prime.
      
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To meet the strict demands for the sea-based aircraft during take-off and landing phase is the most important flight dynamic problem to be solved. One of the main differences between take-off from the ground and from the deck is that ground effect loses gradually after liftoff from the ground,while it loses suddenly in case of liftoff from the deck. As is known to all, the ground effect has considerable influence on drag, down-wash field behind the wing, and specially on lift. The sudden loss of lift may cause...

To meet the strict demands for the sea-based aircraft during take-off and landing phase is the most important flight dynamic problem to be solved. One of the main differences between take-off from the ground and from the deck is that ground effect loses gradually after liftoff from the ground,while it loses suddenly in case of liftoff from the deck. As is known to all, the ground effect has considerable influence on drag, down-wash field behind the wing, and specially on lift. The sudden loss of lift may cause so called "sink" for sea-based aircraft at the instant of liftoff from the deck,which may cause safe problem for aircraft. Two important aspects are included in this thesis:1. A. synthetic method is presented here to estimate ground effects on aerodynamic forces and moments of a complete aircraft.2. The change of take-off characteristics, especially the sinkage, caused by sudden loss of ground effect has been studied and a numerical method concerned has been developed.

众所周知,地面效应(以下简称“地效”)对近地飞行时飞机的迎角、升力、阻力和洗流场都有明显影响,而尤以升力效应对起飞特性的影响最为严重。舰载机在飞离甲板瞬间地效升力突然损失,可能导致“下沉”现象,直接影响到飞机的安全。本文的工作包括两个主要方面:1.在总结现有文献的基础上,提出在不同离陆高度时全机气动参数的计算方法。2.研究舰载机在飞离甲板瞬间因突然失去地效而导致起飞特性的变化,特别是下沉问题。算例表明,地效使得甲板起飞和地面起飞特性有明显区别,是舰载机设计中必须考虑的重要问题。

This paper introduces three parts.The study on the hingemoment balance technoiogy of half model of complete aircraft.Thedesign,research of seven sets of hinge moment balances and four sets ofspecial calibration devices and is tatic calibration of balance.The lastpart is its applications to BOEING 707 model hinge moment test in FD-09 Low-speed tunnel.Tests prove that,the wind tunnel test technoiogy of applying fivesets of hinge moment balances simultaneously on a single model effective-ly saves testing...

This paper introduces three parts.The study on the hingemoment balance technoiogy of half model of complete aircraft.Thedesign,research of seven sets of hinge moment balances and four sets ofspecial calibration devices and is tatic calibration of balance.The lastpart is its applications to BOEING 707 model hinge moment test in FD-09 Low-speed tunnel.Tests prove that,the wind tunnel test technoiogy of applying fivesets of hinge moment balances simultaneously on a single model effective-ly saves testing time and cost,with test efficiency improved.Testresults prove that, the design of hinge moment balance group conformswith the requirements of hinge moment test on half model in Low-speedwind tunnel,with static calibration accuracy higher and dynamic cali-bration results reliable.The resuits from wind tunnel tests are highly appreciated by depart-ments concerned.By comparing the experimental data from FD-09 windtunnei with that from documents,the reliabilty degree of the laterrefrence is,recognized,so this technology is ofimportant refrence valueto the accuracy improvement of hinge moment tests of half model indomestic Low-speed wind tunneis.

本文介绍了全机半模型铰链力矩天平技术的研究;介绍了七台铰链力矩天平和四套专用校正装置的设计和研制;天平的静校及其在 FD-09低速风洞进行的波音707模型的铰链力矩实验。通过实验证明:在一个模型上同时应用多台铰链力矩天平进行风洞实验的技术,有效地节省了试验时间和经费,提高了风洞实验效率。实验结果表明了铰链力矩天平组的设计符合风洞实验的要求,静校精度较高,动校结果可靠。

The aerodynanic design criteria and design procedures for supercritical wing are established based on the computational aerodynamics. For supercritical airfoil design, the criteria contain (a) sonic plateau pressure distribution at off design condition, (b) retarding trailing edge flow separation, (c) near-zero angle of attack at design condition, and (d) local thickness constraints. For supercritical wing design, the criteria include (a) induced drag minimization under some constraints , (b) meeting stability...

The aerodynanic design criteria and design procedures for supercritical wing are established based on the computational aerodynamics. For supercritical airfoil design, the criteria contain (a) sonic plateau pressure distribution at off design condition, (b) retarding trailing edge flow separation, (c) near-zero angle of attack at design condition, and (d) local thickness constraints. For supercritical wing design, the criteria include (a) induced drag minimization under some constraints , (b) meeting stability requirement, (c) isobar pattern on the upper wing surface, and (d) cosidering elastic deformation of two wing. The supercritical wing design procedures can be divided into the phases, i.e. configuration design phase and aerodynamic efficiency optimization phase. The latter contains four steps: (a) basic airfoil design, (b) initial wing design, (c) cruise wing shape design, and (d) jig wing shape design. As a design example, a supercritical wing is designed and is tested in wind tunnel. The result indicates that the complete aircraft with the supercritical wing designed according to the present method has 12% higher cruise efficiency then a typical commercial airliner, although the former wing is 14% thicker than the latter one, which shows the present aerodynamic design method for supercritical wing is practically effective.

以计算空气动力学为基础,提出超临界机翼的气动设计准则和设计流程。翼型设计准则是:非设计状态音速区压力平坦;延迟后缘分离;设计状态迎角接近于零和局部最小厚度约束等。机翼设计准则是:在约束条件下诱阻最小;满足纵向稳定性要求;上翼面等压线型态和考虑结构弹性变形等。设计过程可分为两个阶段,即总体优化和机翼气动设计优化。后者的步骤是基本翼型设计、初始机翼外形设计、机翼巡航外形设计和机翼型架外形设计。对设计实例进行风洞试验后表明:尽管新机翼的平均厚度比某干线运输机厚14%,但安装该机翼的干线运输机巡航效率仍比前者高12%。

 
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