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后缘襟翼
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  “后缘襟翼”译为未确定词的双语例句
     Numercal Simulation of Propeller/High-lift System Interaction
     螺旋桨滑流对带后缘襟翼机翼气动特性影响的数值分析
短句来源
     The work of this thesis is mainly about the design and test of an actuator for a smart rotor with the trailing edge configuration.
     本文对智能旋翼的研究主要是面向真实翼型的主动后缘襟翼智能旋翼驱动器模型设计和试验研究。
短句来源
     Based on wind tunnel tests, this paper deals with the ability and causes of maneuvering flaps to decrease drags, the effects of the flap span, the flap chord, the strake and the wing plane form on the aerodynamic characteristics of the maneuvering flap, the matching of leading-edge and tailing-edge flaps, the improvement in the large angle-of-attack flying quality.
     本文根据风洞实验结果,讨论了机动襟翼减阻的能力和原因,襟翼弦长和展长的影响,前缘襟翼和后缘襟翼的配合使用问题,机翼边条和机翼平面形状对机动襟翼减阻的影响,以及机动襟翼对大迎角飞行品质的改善情况。
短句来源
     The influence of airfoil's leading and trailing flaps' deflection location on aerodynamic efficiency is also discussed primarily.
     初步探讨了二维翼型前、后缘襟翼的偏转位置对气动效率的影响。
短句来源
     The mode is achieved with the symmetric deflection of flaps and aerodynamic decoupling of the change with the angle of attack caused by small disturbances.
     其实现途径是利用后缘襟翼对称偏转所产生的直接力 ,对迎角小扰动变化进行气动解耦 ,从而构成中性稳定舰载飞机 ,使飞机动力学的特征模态由振荡型转变为非周期型。
短句来源
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  相似匹配句对
     Numercal Simulation of Propeller/High-lift System Interaction
     螺旋桨滑流对带后缘襟翼机翼气动特性影响的数值分析
短句来源
     The influence of airfoil's leading and trailing flaps' deflection location on aerodynamic efficiency is also discussed primarily.
     初步探讨了二维翼型前、后缘襟翼的偏转位置对气动效率的影响。
短句来源
     ④Osteophyte formation of the vertebrae.
     4 )椎体后缘骨赘 ;
短句来源
     Development of Tester for Flap Controller
     襟翼控制器检测仪
短句来源
     AERODYNAMIC CHARACTERISTICS OF MANEUVERING FLAPS
     机动襟翼的气动特性
短句来源
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  trailing edge flap
Low cost structural concept for composite trailing edge flap
      
These focused on the trailing edge flap for the transport category aircraft.
      
A single trailing edge flap is used for the purpose of control, and plunge displacement and pitch angle are measured for feedback.
      
A trailing edge flap is hinged at c b after the midchord.
      
An illustration of the effect of trailing edge flap separation for the present configuration is given in sketch J.
      
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  trailing edge flaps
Both the lower surface leading edge and trailing edge flaps improve LID markedly from a lift coefficient grater than 0.28 and 0.4 respectively.
      
However, when trailing edge flaps are extended, some new considerations enter the picture.
      
These trends were noted in previous ground effect studies for aircraft with trailing edge flaps, and similar aspect ratios and wing sweep.
      
These systems are generally quite complex, consisting of a leading edge slat and two or three trailing edge flaps.
      
The aircraft were flown in the baseline configuration as well as with various deflections of leading and trailing edge flaps.
      
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  trailing flap
Characteristics of a trailing flap flow with small separation
      


Many of the current fighter aircraft use maneuvering flaps to enhance air combat maneuverability. Based on wind tunnel tests, this paper deals with the ability and causes of maneuvering flaps to decrease drags, the effects of the flap span, the flap chord, the strake and the wing plane form on the aerodynamic characteristics of the maneuvering flap, the matching of leading-edge and tailing-edge flaps, the improvement in the large angle-of-attack flying quality. This study shows that maneuvering flap is an effective...

Many of the current fighter aircraft use maneuvering flaps to enhance air combat maneuverability. Based on wind tunnel tests, this paper deals with the ability and causes of maneuvering flaps to decrease drags, the effects of the flap span, the flap chord, the strake and the wing plane form on the aerodynamic characteristics of the maneuvering flap, the matching of leading-edge and tailing-edge flaps, the improvement in the large angle-of-attack flying quality. This study shows that maneuvering flap is an effective measure to improve air combat capability of fighter aircraft at large angles of attack. Maneuvering flaps can effectively control the flow Separation and decrease the drag at large angles of attack. They also can expand the buffet boundary and decrease the buffet intensity. As a result, the large angle-of-attack flying quality can be significantly improved by utilization of maneuvering flaps. To the end of optimum comprehensive effect, the effects on both the aircraft structure and the system must be taken into account during the choice of the parameters of maneuvering flaps.

机动襟翼是现代战斗机提高机动格斗能力的常用措施。本文根据风洞实验结果,讨论了机动襟翼减阻的能力和原因,襟翼弦长和展长的影响,前缘襟翼和后缘襟翼的配合使用问题,机翼边条和机翼平面形状对机动襟翼减阻的影响,以及机动襟翼对大迎角飞行品质的改善情况。讨论表明,机动襟翼是提高战斗机空战格斗能力的有效措施。它能控制气流分离和减小大迎角时的阻力,提高抖振边界和降低抖振强度,改善大迎角的飞行品质。为了得到最佳的综合效果,机动襟翼的参数选择必须考虑对飞机结构和系统的影响。

Experimental methods including aerodynamic pressure and force measurements, seven-hole probe survey as well as new technique by using hydrogen bubble and LASER beam for flow visualization were conducted to study the aerodynamic characters of three kinds of vortex flap (i.e. the constant chord, the segmented and the stepped) with 74 degree swept delta wing as a basic planform.It is found that the variation of planforms and geometrical parameters can effect only the drag reduction but little to the low lift in...

Experimental methods including aerodynamic pressure and force measurements, seven-hole probe survey as well as new technique by using hydrogen bubble and LASER beam for flow visualization were conducted to study the aerodynamic characters of three kinds of vortex flap (i.e. the constant chord, the segmented and the stepped) with 74 degree swept delta wing as a basic planform.It is found that the variation of planforms and geometrical parameters can effect only the drag reduction but little to the low lift in low angle of attack conditon. In order to improve the aerodynamic characters, two new devices by adding apex- and trailing-edge flaps on the basic delta wing were studied. Experimental results show that these devices are capable of increasing lift with less drag penalties, if the separated vortices shedding from the apex-flap are kept from break down by properly deflecting the apex-flap.

应用测压、测力、七孔管测速和激光片光源的流态显示等方法对三种(等弦长、分段、台阶)型式涡襟翼进行了实验研究,并和基本翼(74°后掠三角翼)作比较。发现单纯改变涡襟翼的形式和参数能提高减阻效果,但不能改变小迎角下升力过小的现象。为此将机翼前端作成襟翼形式(前端襟翼),并配置后缘襟翼,研究了两种前端襟翼对涡襟翼的干扰,实验证明在某些情况下干扰是有利的,适当控制前端襟翼使分离涡不破裂,可使布局具有减小阻力和增加升力的效果。

Experimental methods including aerodynamic pressure and force measurements,seven-hole probe survey as well as new technique by using hydrogen babble and LASER beam for flow visualization were conducted to study the aerodynamic characters of three kinds of vortex lap (i.e.constant chord,segmented and stepped) with 74 degree swept delta wing as a basic planform.It is found that the variation of planforms and geometrical parameters can effect only the drag reduction but little to the low lift in low angle of attack...

Experimental methods including aerodynamic pressure and force measurements,seven-hole probe survey as well as new technique by using hydrogen babble and LASER beam for flow visualization were conducted to study the aerodynamic characters of three kinds of vortex lap (i.e.constant chord,segmented and stepped) with 74 degree swept delta wing as a basic planform.It is found that the variation of planforms and geometrical parameters can effect only the drag reduction but little to the low lift in low angle of attack condition.In order to improve the aerodynamic characters two new devices by adding apex-and trailing-edge flaps on the basic delta wing were studied.Experimental results show that these devices are capable of increasing lift with less drag penalties,if the separated vortices shedding from,the apex-flap arc kept from break down by properly deflecting the apex-flap.

应用测压、测力、七孔管测速和激光流态显示等方法对三种(等弦长、分段、台阶)型式涡襟冀进行了实验研究,并和基本翼(74°后掠三角翼)作比较。发现单纯改变涡襟翼的形式和参数能提高减阻效果,但不能改变小迎角下升力过小的现象。为此将机翼前端作成襟翼形式(前端襟翼)并配置后缘襟翼,研究了两种前端襟翼对涡襟翼的干扰,实验表明适当控制前端襟翼使分离涡不破裂,可使该布局同时具有减小阻力和增加升力的效果。

 
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