后掠翼的变型是三角翼。
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.
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.
的X - 4的主要参与的重要性，证明1负，在这后掠翼半尾巴设计时并没有接近1马赫的速度合适。
The X-4's primary importance involved proving a negative, in that a swept-wing semi-tailless design was not suitable for speeds near Mach 1.
它采用低雷达截面、变后掠翼、先进航空电子设备以及加力发动机相结合，具有远程、机动性、高效的打击能力。
Its low radar cross-section, variable-geometry wings, advanced avionics, and afterburning engines combine to provide long range, maneuverability, high speed and survivability.
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.
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.
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.
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.
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