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1·The influence of sweep angle and taper ratio on the characteristics of wingtip stalling is discussed.

讨论了后掠角和尖削比这两个机翼外形参数对翼尖失速特性的影响。

2·The arc has a sweep Angle of -180 degrees, which is counterclockwise in the default coordinate system.

这个弧形的散出角度为- 180度，也就是预设座标系统的逆时针方向。

3·An ellipse is defined by its bounding rectangle; an arc is a portion of an ellipse defined by a starting Angle and a sweep Angle.

椭圆是由其边框定义的；弧是椭圆的一部分，由一个起始角和一个扫描角定义。

4·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.

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。

5·The aircraft has a pair of two-section wings, with sweep angle of the inner section larger than the outer section; and two stabilising fins located under the rear fuselage.

飞机有一对双三角翼面，内翼面后掠角比外翼面大，二个稳定翼位于后机身下。

6·Changes of sidewall sweep Angle and cowl position can influence inlet performance such as mass capture, total pressure recovery coefficient and uniformity of isolator exit flow field.

侧板后掠角大小和整流罩位置变化时，对进气道的质量捕获、总压恢复系数和隔离段出口流场的均匀性等都有一定的影响。

7·The influence on flow structure and aerodynamic of a slender by sweep wing at high Angle of attack was studied.

研究了在大迎角下，后掠翼对细长体绕流结构和气动力特性的影响。

8·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。

9·A numerical method to obtain a complete solution of the dynamic response of a variable sweep wing aircraft in the course of changing the angle of sweep is presented in this paper.

本文提出了一套完整的变后掠飞机在变后掠过程中从气动力直至航迹计算的数值求解方法。