猩红的翅膀到了翼端渐变成浅红。
那飞行员使一翼端翘起，以恢复飞机之平衡。
模块化的翼端使炮艇可以根据不同的任务安装专门的附加武器。
Modular wing tips allow the gunship to be fitted with mission specific and additional weaponry.
单襟翼取代了原本双襟翼的设计，同时主体上方额外的翼端帆长度也增加，现在几乎要碰到鼻锥。
A single flap replaces the previous double design and the additional winglets over the main profile have increased in length, almost reaching the side of the nosecone.
在纽柏林，法拉利侧进风口上的翼端帆和冷却用的烟囱被结合成单一物件，进一步强调其空力的作用。
At the nurburgring , the winglets and the cooling chimneys on the ferrari \ ' s sidepods have been combined into one single element , emphasising further their aerodynamic function.
它是由下外侧软骨外侧脚尾侧端，软组织翼，膜性鼻中隔和鼻孔槛共同构成。
It is formed by the caudal edge of the lateral crus of the lower lateral cartilage, the soft tissue alae, the membranous septum, and the sill of the nostril.
已有三个结构在翼缘节点板端部出现了裂纹。
Three structures have exhibited cracking at the ends of flange gusset plates.
“大家都清楚如果你前翼的端板进的碰得到地面，这将是一个巨大的优势。”他补充道，计算表明它一圈可以快一秒。
"It's well known that if you can get the front wing end-plates close to the ground, there's a substantial performance advantage," he added, calculating it could be around a second a lap.
通过对热轧H型钢翼缘端部表面瑕疵进行试验、研究，认为翼缘端部表面瑕疵不影响热轧h型钢的使用。
According to usage the top of flange surface minor faults proceed experiment and study, thought it do not affect HR H-beam.
矿体具体受断裂交汇部位附近的次级短轴背斜轴部、倾伏背斜的倾伏端及其翼部被纵向陡倾角断裂构造所切穿的部位控制，是断裂导矿与背斜构造圈闭的体现。
Controlled by structure trap, ore body located in the core of the brachyanticline or pitch part of plunging anticline which was intersected by high angle longitudinal fault.
随着各裂纹间相互作用的加强，会引起次生裂纹在预置裂隙端部附近反向扩展的现象，并形成一种新的断裂模式——包裹式反翼裂纹。
Then the interaction roles between the flaws gradually become stronger and stronger, and principally, the secondary cracks are induced to extend towards the direction opposite to wing crack.
在两端简支的边界条件下采用分离变量法求解偏微分方程，得到用级数表示的应力解，然后根据剪力滞系数的定义即可得到组合箱梁翼板的剪力滞系数。
Separation of variables is employed to solve the differential equation under the boundary condition of two ends of the girder being simply supported, and the solution of stress is…
根据本发明，后部的线被固定到棒的端部，并且固定到翼的后端。
According to the invention, the rear lines are fixed to the ends of the bar and to the rear ends of the wing.
在两端简支的边界条件下采用分离变量法求解偏微分方程 ，得到用级数表示的应力解 ，然后根据剪力滞系数的定义即可得到组合箱梁翼板的剪力滞系数。
On the basis of mathematical statistic, using the method of multiple regression analysis, the practical calculating formula of the shear lag coefficient in thin-walled curved box girders is derived.
在两端简支的边界条件下采用分离变量法求解偏微分方程 ，得到用级数表示的应力解 ，然后根据剪力滞系数的定义即可得到组合箱梁翼板的剪力滞系数。
On the basis of mathematical statistic, using the method of multiple regression analysis, the practical calculating formula of the shear lag coefficient in thin-walled curved box girders is derived.
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