机翼

机翼显示出金属疲劳的迹象。

The wing of the plane showed signs of metal fatigue .

飞机降落沿跑道滑行的时候机翼擦到了一堆碎石。

As the aeroplane went down the runway the wing touched a pile of rubble .

机翼向下倾斜。

The plane dipped its wings .

机翼在坠机时断裂了。

The aircraft 's wings were sheared off in the crash .

他注意到机翼在一块一块地断裂。

He noticed that fabric was tearing away from the plane 's wing

机翼与航线成直角。

The wings were at right angles to the line of flight .

飞机的两个机翼遭受撞击折断了。

The two wings of the aircraft broke off on impact

拆除机翼和机尾，将飞机改装成汽车，前后要花15分钟。

It takes 15 minutes to convert the plane into a car by removing the wings and the tail

这样可防止机翼结冰。

That will prevent the wings of the aircraft from icing up .

机翼显出有金属疲乏的迹象。

The airplane wing showed signs of metal fatigue .

飞机的机翼很长。

The plane 's wings are very long .

美国航空公司发言人说，飞机降落装置的某些部分损毁，右侧的一个发动机在撞击下从机翼上脱落。

A spokesman for American Airlines says part of the plane 's landing gear collapsed , and one engine on the right side fell off the wing from the impact .

但要实现所有这些概念花销巨大，需要陆上和空中的安全认证标准，需要双重控制，需要复杂的折叠机翼和螺旋桨，还得从飞机跑道起飞。

But all these concepts are massively expensive , require safety certification standards for road and air , need dual controls , involve complex folding wings and propellers , and have to be flown from air-strips .

提出采用H二滤波实现姿态匹配传递对准，解决了在载机机翼弹性变形建模不准或不易建模的情况下，姿态匹配传递对准的实现问题。

The H ∞ filtering of the attitude matching transfer alignment is presented .

本文发展了一种面元法（PanelMethod），用以计算具有脱体涡的三元厚度机翼的空气动力。

The present paper has developed a panel method predicting the non-linear aerodynamic loads on thick wings with separation vortices .

机翼跨声速绕流的Galerkin有限元解法

Galerkin finite element method for transonic flow about airfoils and wings

基于N-S方程的弹性机翼载荷分析方法研究

An Analysis Method of Loads on Aircraft Elastic Wing with Its Real Deformation Considered

带有襟翼偏转的三维机翼绕流的N-S方程解

N-S solution of a 3d wing with flap

本文试图用一种新的加工方法&纤维缠绕（FW）来成型机翼蒙皮。

The paper tries to adopt a new method-FW to mould it .

这机翼是用一种使用了stratasys的3d打印机的热塑性材料制成的。

The wing was made from a thermoplastic material using a STRATASYS 3D printer .

采用激光粒子成像速度仪（PIV）对一矩形机翼（NACA0012）模型所产生的翼梢涡进行了风洞测试研究。

Tip vortices generated from a rectangular half-span wing model ( NACA 0012 ) have been experimentally investigated .

给出了一种带副翼偏转的三维机翼分区网格及绕流的Euler方程解。

A zonal patched grid for a wing with control surface deflection and Euler solution for the flow around the wing are also given .

机翼和叶栅非定常流的Kutta条件

Kutta Condition in Unsteady Flow Around Airfoils and Cascades

最后，通过计算三维复杂目标金属机翼目标的RCS，给出并行加速比和并行效率的测试结果。

The radar cross sections ( RCS ) of complex objects of metallic wing and NASA almond and practical object of missile are presented .

描述了应用PIV技术在水槽中对边条机翼上旋涡及破裂旋涡流场进行的测量和分析。

In this paper measurement result and analysis concerned with vortex flow and bursting vortex flow over a strake-wing are presented .

研究结果表明，机翼形量水槽可以作为一种新型的U形渠道量水设施，具有一定的实际应用价值。

The studying result show that the plane wing form measuring water slot can be a kind of new U channel measuring water facilities , certainly have actual application value .

再基于Ansys有限元法对机翼结构进行强度分析，确定了定量指标，有效的发现了危险地来源，抓住危险控制的关键项目。

The strength analysis of the wing structure through the Ansys finite element method , determines the quantitative indicators , effectively discovers the hazard source and seizes control of key projects .

飞机机翼纤维缠绕（FW）运动规律分析及控制系统研究

FW , in round taper pot74 ; The Research of Filament Winding Motion Rule and Control System for the Airfoil

为了验证方法和程序的正确性，论文中对M6机翼和F4翼身组合体的流场进行了数值模拟，并与试验结果进行了对比。

The viscous flow around M6 wing and F4 wing-body configuration are simulated and compared with the results of wind tunnel experiment .

本文使用了有限体积法进行空间离散，双时间法进行时间推进，五步Rung-Kutta法进行伪时间的积分来求解运动机翼的非定常流场；

The solution of unsteady flow employs a finite-volume method and 5-step Rung-Kutta scheme .