它们又长又细的尾巴配合后掠式的襟翼，完美地适用于最省力的方式提供推动力。
Their high, narrow tails with swept-back tips are almost perfectly adapted to provide propulsion with the least possible effort.
膝关节适度后掠，第二节大腿清晰。
后掠上置尾垂翼连同一个后掠锥形尾平翼。
The tail flats are high-mounted, swept-back with a swept-back and tapered fin.
后掠翼的变型是三角翼。
并对后掠叶片叶轮流场好的原因作了分析。
Moreover, the reason why a good flow field exists in the impeller with backward swept blades is also explained.
它倏地斜着后掠的双翅俯冲，然后又盘旋起来。
He made a quick drop, slanting down on his backswept wings, and then circled again.
给出一种可展曲面后掠叶片离心式压气机叶轮选型方法。
A geometry designing method for developable surfaces backward swept centrifugal compressor was given in this paper.
结果表明，压气机转子前缘激波后掠可以有效地降低损失。
The result shows that the leading edge shock wave sweepback could reduce loss obviously.
本文介绍一种具有后掠叶片的径流式压气机叶轮造型方法。
This paper puts forward a method for designing the backward swept blades for centrifugal compressor impellers.
该控制器应用于变后掠机翼的结构强度加载控制系统之中。
This controller is applied to the structural strength loading control system, which is the experimental system of a variable swept aircraft wing.
后掠会增加效率，但是会降低喘振裕度，而前掠有相反的趋势。
Backsweep can improve the efficiency at the expense of surge margin.
本文应用三元亚音速升力面理论求出了后掠翼前缘附近的流场。
The unsteady flow field near the leading edge of an oscillating sweptback wing is obtained by using 3-D subsonic lifting surface theory.
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。
The influence on flow structure and aerodynamic of a slender by sweep wing at high Angle of attack was studied.
这种方法不需要计算出无粘流线的细节，并适用于不同外形的后掠翼。
The method does not require to calculate the details of the stream lines and can be used for various swept wings at moderate angle of attack or yaw angle.
空客的设计展示出了一个在高速和低速飞行时减少后掠的更好的机身外貌。
They give a better performance, with less sweepback, at high and low speeds.
得出的图片突出显示了星际尘埃和气体群的轮廓所形成的明亮的后掠式突起。
The resulting image highlights the bright swept-back ridges that outline pockets of cool interstellar dust and gas.
作为算例用它计算了后掠超音速平板叶栅由于振动引起的非定常空气动力功。
Program and unsteady aerodynamic work caused by oscillation of sweepback supersonic plate cascade were provided as an example of its application.
在贝尔x - 5和空军赋予的NACA研究人员一个机会来测试可变后掠翼。
The Bell X-5 gave NACA and Air Force researchers a chance to test out variable-sweep wings.
以动力学模型和气动模型相匹配为原则，建立了后掠桨尖旋翼的细致气弹模型。
A refined aeroelastic model of a helicopter rotor blade with swept tips is established based on model matching.
尾平翼特征是顶端有一个上端后掠的垂直安定翼和锥形尾垂翼具有一个钝形顶端。
The tail flats feature swept-back tips forward of the swept-back and tapered fin with a blunt tip.
我们有各式各样的发型，如：迷你式、高贵式、马尾式、后掠式、盘发式、齐肩式等等。
We have various kinds of patterns, such as mini style, noble style, horse-tail style, hair sweptback, chaplet hair style, shoulder length hair style and so on.
我们有各种各样的发型，如剪短发、后掠式、盘花冠式、齐肩式，还有把头发挽成发髻。
We have various models: hair bobbed, hair sweptback, chaplet hair style, shoulder-length hair style, hair done in a bun.
压缩性的影响本文不采用P—G转换，而是直接使用可压缩空间后掠马蹄涡和源(汇)。
In this paper, the effect of compression does not be treated with PrandtI-Glauert's transformation, bat directly treated with compressible source (sink) and vortex.
我们有各种各样的发型，如剪短发、后掠式、盘花冠式、齐肩式，还可以把头发挽成发髻。
We have various models: hair bobbed, hair sweptback, chaplet hair style, shoulder-length hair style, hair done in a bun.
我们有各式各样的发型，如剪短发、后掠式、盘花冠式、齐肩式，还可以把头发挽成发髻。
We have various styles: hair bobbed, hair swept back, chaplet style, shoulder-length, hair done in a bun.
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。
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.
尾梁从机身渐细到后掠尾垂翼，尾螺旋桨在锥形尾垂翼右侧，二个尾平翼被装在尾梁两侧。
The tail boom tapers from the main body to the swept-back, tapered fin with a rotor on the right. Two flats are mounted on the both side of the boom.
用该系统对某级增压比2.2的单级高负荷后掠风扇进行了后掠和前掠大小叶片改型设计。
Using this design system, a high-loaded backward-swept fan with a stage pressure ratio of 2.2 was redesigned firstly as a backward-swept and secondly as a forward-swept splittered fan.
用该系统对某级增压比2.2的单级高负荷后掠风扇进行了后掠和前掠大小叶片改型设计。
Using this design system, a high-loaded backward-swept fan with a stage pressure ratio of 2.2 was redesigned firstly as a backward-swept and secondly as a forward-swept splittered fan.
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