片语

landing lift coefficient着陆升力系数

flight lift-coefficient range飞行升力系数范围

cushion lift coefficient气垫升力系数

blade-lift coefficient桨叶升力系数

lift drag coefficient零升力阻力系数

zero lift drag coefficient零升力时阻力系数

of zero-lift drag coefficient零升力阻力系数

lift force coefficient升力系数

英汉例句

• hydrodynamics shows that the flap rudder can increase lift coefficient notably.

  水动力学表明，襟翼舵的存在大幅度地提高了升力系数值。

• on this type of airfoil vortex generators (also called micro-vortex generators, or vgs) add very little improvement with respect to the maximum lift coefficient (or stall speed).

  对这种类型的翼型涡发生器（也称为微型涡发生器，或vgs ）添加很少的改善方面的最高升力系数（或失速速度） 。

• when twin vertical fins are located at the wing surface the maximum lift coefficient could be increased obviously and the incidence range of yawing and rolling stability is extended.

  当双立尾分别移到机身外侧置于机翼上时，可以显着提高全机最大升力系数，同时使航向和滚转稳定的迎角范围大为扩展。

• experiment results indicate that the flexible wing has a larger angle of stall and a greater maximum lift coefficient than the fixed wing.

  对比结果表明：柔性翼相比于对应的刚性翼，失速迎角较大；

• predicted pressure distribution and lift coefficient are in agreement with numerical results and experimental data available in the literature.

  压强分布和升力系数的计算值与现存文献的数值结果和实验数据是一致的。

• the lift coefficient can thus be effectively doubled with relatively simple devices (flaps and slats) if used on the full span of the wing.

  该升力系数因此，可以有效地增加一倍，相对简单的装置（襟翼和缝翼） ，如果使用对充分跨度机翼。

• however, by combining the use of trailing-edge flaps with leading-edge slats, the wing「s lift coefficient can be effectively doubled if used on the full span of the wing.

  然而板条，结合边缘皮瓣与领先使用的后缘，机翼的升力系数，可有效地增加一倍，如果用在机翼完整的跨度。

• the riblet structure has almost no influence on the lift coefficient and pitching coefficient of model.

  脊状结构的存在对模型升力系数和俯仰力矩系数几乎没有影响。

• the unique aim of aerodynamic designer is always to enhance lift coefficient and reduce drag coefficient.

  增升减阻一直是空气动力设计工作者追求的目标。

• when the ratio of height to width increases, the lift coefficient aggrandizes, and the drag coefficient diminishes.

  其高宽比增加，升力系数增大，阻力系数减小。

• by this study , we confirm the method of blowing control of wind tunnel side wall layer , especially when the airfoil experiment is to get the bigger lift coefficient .

  以上结论说明风洞侧壁附面层吹除控制对翼型试验是有效的，特别对带襟翼的高升力翼型试验效果是显着的。

• the maximum lift coefficient could be raised by 30%. it has been shown that moving surface is an excellent technique to control separated flow over the strake wing.

  结果表明，在这种机翼上转动前缘对控制分离是有效的，升力增量最大可达30％。

• besides, the lift coefficient of the downstream cylinder increases linearly with angular deviation in a suitable range of spacing and angular deviation.

  此外，后柱升力系数也在一定范围内随气流偏角而线性增长。

• we take the maximum lift coefficient as the objective function. this approach is used to calculate the maximum lifts of nlr 7301 airfoil and ga(w)-l airfoil.

  以最大升力系数为目标函数，对前缘缝翼或襟翼的位置和偏角进行优化。

• the oscillating lift coefficient increases with the growth of the void fraction in such a way that it increases slowly before the void fraction up to 0.1 and after that, increases faster.

  脉动升力系数先随含气率的增大而缓慢增加，在含气率增大到0.1后增大得较快。

• in this paper, a semi-empirical prediction method of maximum lift coefficient at low subsonic speeds for wings/bodies with high aspect ratio is investigated.

  本文研究了大展弦比机翼／机身低亚声速最大升力系数的半经验预测方法。

• as the growth of the cross section of the rectangle inlet, the lift coefficient varies little, but the drag coefficient increases dramatically.

  矩形进气道横截面积增加，对升力系数影响不大，但阻力系数增加明显；

• the joined-wing configuration, as compared with the normal configuration, is characterized by low structural weight, small induced drag, big lift coefficient and good stability.

  联结翼布局与常规布局相比具有结构重量轻、诱导阻力小、升力系数大和稳定性良好的特点。

• the experimental results show that the maximum lift coefficient cy max and stall incidence are increased with increased pitch up rate, when the wing is rapidly pitching up.

  结果表明：机翼快速上仰时，随上仰速率增大最大升力系数增高，即动态升力效应更明显；

• since this method adopts non-linearized theory of the lift coefficient curve of the blade section and multiple streamtube model, and has revised the aspect ratio influence, so it has wide suitability.

  这个方法采用了叶型升力曲线的非线性理论和多流管的理论模型，并对展弦比的影响进行了修正，从而具有广泛的适用性。

• after aerodynamic optimization of an unmanned vehicle with the methods mentioned above, the lift coefficient has an increase of 21 % and the ratio of lift to drag has an increase of 6. 7%.

  通过优化无人机外形取得了有意义的结果，优化后升力系数增加了21％，升阻比提高了6．7％。

• the stall of the wing occurs at the highest lift coefficient on an airfoil, when the airflow can no longer go around the airfoil」s nose (leading edge) and separates from the upper wing surface.

  机翼失速的发生在电梯表面系数最高的机翼上，当气流不能继续围绕翼型的鼻子（领先），并脱离机翼上。