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有效迎角
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  effective angles of attack
     According to known effective angles of attack and Reynolds number, we will get the corresponding second value of spanwise lift and the moment distribution of wing from exprimental data of airfoil aerodynamic characteristics.
     然后根据有效迎角及雷诺数,从翼型实验数据得到相应的升力和力矩分布的第二次近似值。
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  “有效迎角”译为未确定词的双语例句
     The mechallism of the pivot effect on the dynamic hysteresis characteristics were probed mainly due to the dynamic wash effect during pitching up or down and changing local efficient angle of attack, which affected the dynamic vortices and their developing.
     转轴位置对动态迟滞特性的影响可以认为主要是由于俯仰运动时的动态洗流影响所导致的实际有效迎角的变化,由此影响了动态分离涡及其发展。
短句来源
     The results of the numerical calculation showed that the thrust and the maximum effective attack angle were related to the phase difference between heaving and pitching.
     机翼做沉浮/俯仰联合运动时,尾迹中总是出现逆Karman涡街。 结合数值计算结果说明,机翼做沉浮/俯仰联合运动时,推力及最大有效迎角与沉浮和俯仰运动之间的相位差有关。
短句来源
     The torsion reduces the effectual attack angle of the elastic sweep wing.
     有效迎角的减小又使得弹性机翼的有效气动力载荷减小。
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  相似匹配句对
     all effective.
     全部有效
短句来源
     From Effective ness to Success
     从有效到成功
短句来源
     The torsion reduces the effectual attack angle of the elastic sweep wing.
     有效迎角的减小又使得弹性机翼的有效气动力载荷减小。
短句来源
     THE METHOD FOR EXTENDING THE RANGE OF ATTACK ANGLE AND BLOCKAGE IN TRANSONIC WIND TUNNEL TESTING-USING LOW SUPERSONIC NOZZLE IN STEAD OF SONIC NOZZLE
     提高大迎角跨声速风洞实验堵塞度的有效途径——采用低超声速喷管
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  effective angle of attack
At the end of a stroke the wings move up again which leads to a decrease in effective angle of attack.
      
At subsonic Mach numbers, decreases with increasing effective angle of attack.
      
However, the effective angle of attack is altered such that the deviation leads to leveling of the force distribution.
      
It appears that the deformation allows the wing to experience a smaller effective angle of attack at high vehicle attitudes.
      
In all cases the effective angle of attack was constant and equal to 2.57 degrees.
      
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In this paper, an approximate method is presented to compute low-speed aerodynamic characteristics of high-middle aspect ratio and low sweep angle wing with separation. For given plane forms and geometrical angles of attack wing, we use the linear lifting surface theory to compute the first value of spanwise lift and the moment distribution of wing, and we adversely apply the linear lifting surface theory to the computation of the downwash flow field. So we will gain effective angle of attack at each wing section.According...

In this paper, an approximate method is presented to compute low-speed aerodynamic characteristics of high-middle aspect ratio and low sweep angle wing with separation. For given plane forms and geometrical angles of attack wing, we use the linear lifting surface theory to compute the first value of spanwise lift and the moment distribution of wing, and we adversely apply the linear lifting surface theory to the computation of the downwash flow field. So we will gain effective angle of attack at each wing section.According to known effective angles of attack and Reynolds number, we will get the corresponding second value of spanwise lift and the moment distribution of wing from exprimental data of airfoil aerodynamic characteristics. Iteration is done again and again until convergence is reached.

本文介绍一种计算带分离的大中层弦比、小后掠角机翼低速气动特性的近似方法。根据给定机翼的平面形状和几何迎角,按线化升力面理论算出升力和力矩沿展向分布的第一次近似值。再逆向应用升力面理论估算下洗流场,从而近似地得到各个削面的有效迎角。然后根据有效迎角及雷诺数,从翼型实验数据得到相应的升力和力矩分布的第二次近似值。如此反复迭代直至收敛为止。

An analytical method is described for the fluid flows of the cross wings of a missile at angles of attack and yaws according to the analyses of the results for the flow visualization studies in a water channel. It is noted that there are very different effective angles of attack and effective swept angles of leading edges for the four cross wings and then different effects on the fluid flows and their aerodynamics. It is supposed to be helpful for analysing the efficiency of control surfaces of the cross wings...

An analytical method is described for the fluid flows of the cross wings of a missile at angles of attack and yaws according to the analyses of the results for the flow visualization studies in a water channel. It is noted that there are very different effective angles of attack and effective swept angles of leading edges for the four cross wings and then different effects on the fluid flows and their aerodynamics. It is supposed to be helpful for analysing the efficiency of control surfaces of the cross wings and therefore the guide of the missile. Also it is useful setting the computational model of a missile with cross wings.

本文从流态结果的研究出发提出对导弹“×”翼状态翼面流动的分析方法,指出有迎角和侧滑角情况下四片翼面各不相同的有效迎角和前缘有效后掠角对于翼面流动以及气动力的影响。本文的分析方法对于分析“×”翼在有迎角和侧滑角情况下的操纵面效能及其导弹的制导有一定的帮助,也可以为有关计算模型的建立提供一些物理依据。

The pivot effects on dynamic hysteresis characteristics were studied by pitching wing, body and three kinds of wing-body combina- tions. Very important effects of the piyot positions on dynamics hyster-esis characteristics appeared. The dynamic hysteresis behaviors were serious as the pivot position moved backward on the wing. Also similar behaviors appeared on the body as the pivot position was far from the tip of body. Three kinds of wing body combinations were used for investiga- ting the pivot effect on...

The pivot effects on dynamic hysteresis characteristics were studied by pitching wing, body and three kinds of wing-body combina- tions. Very important effects of the piyot positions on dynamics hyster-esis characteristics appeared. The dynamic hysteresis behaviors were serious as the pivot position moved backward on the wing. Also similar behaviors appeared on the body as the pivot position was far from the tip of body. Three kinds of wing body combinations were used for investiga- ting the pivot effect on the wings of the combinations. Much more serious dynamic hysteresis appeared on the wing ahead of the pivot and the dynamic stall occured on the canard later. Opposite hysteresis behaviors appeared on the wing behind of the pivot. It is supposed that the dyna- mic stall appeared on the tail early. The mechallism of the pivot effect on the dynamic hysteresis characteristics were probed mainly due to the dynamic wash effect during pitching up or down and changing local efficient angle of attack, which affected the dynamic vortices and their developing.

研究了转轴位置对机翼、机身和三个组合体上翼面的动态特性的影响。对于机翼和机身,当转轴位置后移时其动态迟滞效应更为强烈。当翼面处于转轴之前,上仰时会出现更为严重的动态迟滞效应,因此鸭翼达到动失速状态较晚。而当翼而处于转轴之后时,如尾翼,将会更早地出现动失速。转轴位置对动态迟滞特性的影响可以认为主要是由于俯仰运动时的动态洗流影响所导致的实际有效迎角的变化,由此影响了动态分离涡及其发展。

 
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