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边条涡
相关语句
  strake vortex
     USING STRAKE VORTEX TO REDUCE THE DISTORTION OF A Y SHAPED INLET
     利用边条涡抑制Y形进气道流场畸变
短句来源
     Wing-inboard vortex make strake vortex move down. Strake vortex make wing-inboard vortex move outside and increase the wing-inboard vortex's intensity. Both of them improve the wing's vortex lift.
     研究表明机身边条在攻角12°以后使升力有了很大提高,这是由于机身边条产生的边条涡在一定迎角下与内翼涡相互诱导、相互作用,内翼涡使边条涡向机翼内侧移动,而边条涡则将内翼涡向外推,并使内翼涡的强度增大,两者的作用提高了双三角翼内翼上的涡升力,起到增升的作用。
短句来源
     Results indicate that the strength of the strake vortex increases with a quadric function of the attack angle and the type of vortex breakdown is spiral breakdown in this experiment.
     实验结果表明边条涡强度随攻角呈平方关系增长 ,边条涡的破碎形态为单螺旋破碎。
短句来源
     CHARACTERISTICS OF CANARD VORTEX INTERACTION WITH STRAKE VORTEX AT HIGH INCIDENCE
     大迎角下鸭翼涡与边条涡的干扰特性
短句来源
     Induction between the canard vortex, located at the wing inboard, and the strake vortex with each other resulted in deflection of the strake vortex to the wing outboard. The deflection not only improved the wing outboard flow condition but also made the wing leading edge vorticity twist into strake vortex, which increased the strake vortex's intensity and delayed the strake vortex's burst.
     鸭翼涡位于机翼内侧 ,其与边条涡的相互诱导致使边条涡向外翼偏折 ,既改善了外翼的流态 ,又使机翼前缘涡量卷入边条涡 ,增强了边条涡的强度 ,从而延迟其破裂。
短句来源
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  “边条涡”译为未确定词的双语例句
     An Experimental Investigation on Properties of Strake Vortices Using Particle Image Velocimetry
     用粒子图像测速法研究边条涡的性质
短句来源
     Especially in high angle of attack the streak vortex in upper wing surface interfered with free vortex of canard wing and main vortex of wing formed nonlinear lift by synthesising of three vortices together,and greatly improved the flow characteristics for whole aircraft.
     特别在大攻角时,边条涡处在机翼上表面与鸭翼自由涡和机翼主体涡相干涉,形成了三涡一体的非线性升力,极大地改善了全机的流动特性。
短句来源
     Moreover, for the scatter of the experimental pitch up moment curve in the case of natural transition, the explanation has been made.
     另外 ,对自由转捩条件下 ,俯仰力矩曲线在α =35°~ 70°之间很分散的风洞实验结果进行了初步的解释 :α =35°基本上对应于边条涡非对称破裂的开始 ;
短句来源
     The technology of strake wings that has been applied to control external flows was employed firstly in the control of internal flows in this paper, in order to reduce the distortion of a Y\|shaped inlet and improve the inlet\|engine compatibility.
     已用于飞机外流流场控制的边条涡技术被首次引入内流场的控制 ,抑制进气道出口流场畸变 ,改善进发匹配。
短句来源
     An experimental investigation on the properties of vortices generated by the strake-wing has been carried out in the wind tunnel using Particle Image Velocimetry (PIV).
     在风洞中应用粒子图像测速法对边条机翼模型产生的边条涡的各种特性进行了实验研究。
短句来源
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  相似匹配句对
     STUDIES ON STRAKE-WING AERODYNAMICS AND SEPARATED VORTEX
     边条翼及分离研究
短句来源
     An Experimental Investigation on Properties of Strake Vortices Using Particle Image Velocimetry
     用粒子图像测速法研究边条的性质
短句来源
     A STUDY OF GROUND VORTEX
     地面研究
短句来源
     The concept of vortex vibration was put forwarded.
     提出振概念;
短句来源
     (2)deal with regulas easily;
     (2 )极易处理边条 ;
短句来源
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  lex vortex
It is recognised that prediction of buffet loading requires accurate modelling of the unsteady pressure field past a burst LEX vortex.
      
The work is concerned with the computation of F/A-18 vertical tail buffet due to LEX vortex burst using vortex methods of unsteady flow modelling.
      
  strake vortex
Along with the striations the vapor screen images show a ring of condensation around the primary condensations pattern of the strake vortex.
      
At a Mach number of 0.90, the development of strake vortex is clearly seen to occur between 9.38 and 11.39 degrees angle of attack.
      
Baseline configuration PSP pressure map images at Mach 0.7 clearly show striations on the strake vortex footprint.
      
It is hypothesized this is caused by a delay of the strake vortex entrainment by the wing vortex.
      
Increasing Mach delays the entrainment of the strake vortex by the wing vortex.
      
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An experimental investigation to delay wing vortex bursting for fighter and missile-type wing-body combination was carried out by means of flow visualizations and force measurements. Both wings of the experimental models had sharp leading-edge. The body-strake with high sweepback and small area was fixed to both sides of the body. The fighter-type model had a delta body-strake with 70 deg. sweepback angle, 10.2% of the exposed wing span and 2.2% of the exposed wing area. There were three strake positions along...

An experimental investigation to delay wing vortex bursting for fighter and missile-type wing-body combination was carried out by means of flow visualizations and force measurements. Both wings of the experimental models had sharp leading-edge. The body-strake with high sweepback and small area was fixed to both sides of the body. The fighter-type model had a delta body-strake with 70 deg. sweepback angle, 10.2% of the exposed wing span and 2.2% of the exposed wing area. There were three strake positions along the vertical direction of the body, i.e. the higher position, the middle one and the lower one. The vortex flow pattern visualization of models with and without body strake are presented in the paper. The comparison of these flow patterns indicates that the vortex bursting of the wing for model with body-strake is delayed efficiently. Longitudinal force and moment data were obtained for the fighter model and comparison between experimental results with and without body-strake were given graphically. It illus trates that the effect of the body-strake can increase actually the maximum lift coefficient and that to some extent the critical angle of attack.Experimental result also shows that the drag coefficient has some increment in the presence of body-strake over the range of angle of attack; when a<10°, the lift-drag ratio is decreased, but a>°, the body-strake has not effect essentially on lift-drag ratio. As using the body-strake, the longitudinal static stability must be considered, be-cause it is decreased.

本文通过测力和水槽流态观察试验研究了战斗机和导弹式的翼体组合体翼涡破裂的推迟措施。利用安置于机翼(弹翼)前方和机体两侧的大后掠、小面积的机体边条所产生的边条涡的有利干扰,可以有效地推迟翼涡的破裂,从而达到提高最大升力系数和临界迎角的目的,试验表明,安置在不同位置的机体边条均可不同程度地提高最大升力系数C_(Lmax),在适当位置时,可提高临界迎角α_(kp)达2°~3°。

This paper present a new design of a pilotless aircraft with good performance of both aerodynamic and stealth by use of stealth contour technology to constitute a new aerodynamic configuration layout.The method applied in aerodynamic design are as follows: A small aspect ratio and high sweepback blended wing body configuration with streak are used to improve the flow field in the root wing, and through the streak vortex stabilized the separated vortex in the nose of fuselage; To fix canard wing reasonably for...

This paper present a new design of a pilotless aircraft with good performance of both aerodynamic and stealth by use of stealth contour technology to constitute a new aerodynamic configuration layout.The method applied in aerodynamic design are as follows: A small aspect ratio and high sweepback blended wing body configuration with streak are used to improve the flow field in the root wing, and through the streak vortex stabilized the separated vortex in the nose of fuselage; To fix canard wing reasonably for making its vortex flow over wing in order to increase the vortex strength in upper wing then the vortex separation in the wing surface delays so as to get nonlinear lift of wing. Especially in high angle of attack the streak vortex in upper wing surface interfered with free vortex of canard wing and main vortex of wing formed nonlinear lift by synthesising of three vortices together,and greatly improved the flow characteristics for whole aircraft.The test proved that, this pilotless aircraft configuration has the advantage of high lift curve slope,high lift/drag ratio,high stalling angle and excellent longitudinal and lateral stability with comparison of the analogous ordinary configuration. The model measurement in an enechoic chamber proved that,the new project has also low RCS value in the front sector and in lateral sector.

应用棱边边条和小展弦比大后抗角机翼融合设计,使边条涡稳定机头的脱体涡改善机翼根部流场;同时合理配置前翼,使鸭翼产生的涡流流经机翼时,加强了机翼上表面的主体涡流强度,推迟了机翼表面流态分离,提高了机翼的非线性升力。特别在大攻角时,边条涡处在机翼上表面与鸭翼自由涡和机翼主体涡相干涉,形成了三涡一体的非线性升力,极大地改善了全机的流动特性。经实验证明,该布局提供的方案,具有与同类普通布局为高的升力线斜率、高升阻比、大失速攻角及良好的纵横向和侧向静安定性等优点,同时通过电磁模型在微波暗室中测试,在迎头和侧向的RCS值(雷达反射截面)均有明显的下降。

The dye injection flow visualization technique has been used to study the changes of flow patterns for a simplified aircraft model with the variation of angles of attack and the incoming flow velocity in a water tunnel. In this experiment, the changes of flow patterns do not have essential difference at several incoming flow velocities, but the variation of the relevant angles of attack occurs indeed, which means that there exists the Re dependence. Moreover, for the scatter of the experimental pitch ...

The dye injection flow visualization technique has been used to study the changes of flow patterns for a simplified aircraft model with the variation of angles of attack and the incoming flow velocity in a water tunnel. In this experiment, the changes of flow patterns do not have essential difference at several incoming flow velocities, but the variation of the relevant angles of attack occurs indeed, which means that there exists the Re dependence. Moreover, for the scatter of the experimental pitch up moment curve in the case of natural transition, the explanation has been made. α =35° corresponds the start of asymmetric breakdown of the strake vortex and α =70° is the critical point of the flow forth and back in the up wind side of the nose.

在水洞中应用染色液流动显示技术对某型号飞机简化模型机头流动状况随攻角和来流速度的演化进行了观测和分析 .实验结果表明 ,在本实验条件下 ,对于不同的来流速度或雷诺数 ,每种流动现象所对应的攻角确实发生了变化 ,说明雷诺数的影响确实存在 ;另外 ,对自由转捩条件下 ,俯仰力矩曲线在α =35°~ 70°之间很分散的风洞实验结果进行了初步的解释 :α =35°基本上对应于边条涡非对称破裂的开始 ;而α =70°则对应于机头迎风面流动向前、向后的临界点

 
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