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   垂向阻力 的翻译结果: 查询用时:0.201秒
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垂向阻力
相关语句
  vertical drag
     When helicopter is in hover, aerodynamic interference between main rotor and fuselag induces maily increase of fuselag vertical drag.
     直升机在悬停时旋翼/机身的气动干扰,主要引起机身垂向阻力的增加。
短句来源
     The paper is base on reference and gives theory method for estimating vertical drag, and for example of one helicopter, lias computed,Obtains a good agree of computing result with main rotor/fuselag wind tunnel lest result.
     本文根据参考文献,给出估算垂向阻力的理论方法,并以某机为例进行了计算,计算结果与该机的旋翼/机身组合风洞试验结果相比,获得了很好的一致。
短句来源
  相似匹配句对
     Overcome the Hardships
     战胜阻力
短句来源
     Resistance of Alluvial Channel
     冲积河床阻力
短句来源
     The numerical simulations show that the preloading along the orthogonal direction would cause stress degradation in soils and induce orthogonal loading effect.
     研究结果表明,垂直方向的预加载会引起土阻力的退化,产生“垂向加载效应”;
短句来源
     When helicopter is in hover, aerodynamic interference between main rotor and fuselag induces maily increase of fuselag vertical drag.
     直升机在悬停时旋翼/机身的气动干扰,主要引起机身垂向阻力的增加。
短句来源
     THE TRACK OF OIL AND GAS VERTICAL MIGRATION
     油气垂向运移的形迹
短句来源
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  vertical drag
The degree of anisotropy in the vertical drag was shown to vary with the element Reynolds number.
      


When helicopter is in hover, aerodynamic interference between main rotor and fuselag induces maily increase of fuselag vertical drag. The paper is base on reference and gives theory method for estimating vertical drag, and for example of one helicopter, lias computed,Obtains a good agree of computing result with main rotor/fuselag wind tunnel lest result.

直升机在悬停时旋翼/机身的气动干扰,主要引起机身垂向阻力的增加。本文根据参考文献,给出估算垂向阻力的理论方法,并以某机为例进行了计算,计算结果与该机的旋翼/机身组合风洞试验结果相比,获得了很好的一致。

The results of rotors/fuselage aerodynamic interactions for the coaxial helicopter in hovering and forward flight were presented according wind-tunnel experiment. The presence of the rotor wake creates a significant down load on the fuselage which decreases with increasing advance ratio. The interactions above decreased in forward flight, but yaw moment was generated by fuselage; The interaction of coaxial rotors to fuselage changes when the tail plane area, and lower rotor pitch or advance ratio was changed....

The results of rotors/fuselage aerodynamic interactions for the coaxial helicopter in hovering and forward flight were presented according wind-tunnel experiment. The presence of the rotor wake creates a significant down load on the fuselage which decreases with increasing advance ratio. The interactions above decreased in forward flight, but yaw moment was generated by fuselage; The interaction of coaxial rotors to fuselage changes when the tail plane area, and lower rotor pitch or advance ratio was changed. The interaction of fuselage to coaxial rotors is different from that of single rotor helicopter, such as: in hovering state, the coaxial helicopter fuselage has no obvious effect on rotors, the fuselage generates beneficial interaction to coaxial rotors when in forward flight and the interaction decreases as the advance ratio increases.

介绍了由风洞实验得到的共轴式直升机在悬停和前飞时旋翼 /机体气动干扰结果 ,并与单旋翼直升机进行了比较 .旋翼对机体的干扰主要表现为 :悬停时机体上产生垂向阻力和俯仰力矩 ;前飞时上述干扰减小 ,但机体的纵向和航向气动特性发生变化 ;分别增大水平尾翼面积和下旋翼桨距 ,旋翼对机体的干扰量增大 ;悬停时 ,机体对旋翼无明显影响 ,前飞时产生有利干扰

 
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