试验给出机身对称面、翼前缘、立尾前缘等处的热流率分布。
The heat flux distribution is provided at the asymmetric side of the body, wing and the vertical fin.
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.
翼上初级飞羽呈现灰白色，翼前缘经常为淡棕色或黄棕色，比飞羽的深灰色要浅。
Upperwing has pale greyish-white primary bases and often pale rufous or yellowish-brown forewing, paler than dark grey flight-feathers.
防冰系统可防止冰在缝翼前缘堆积，此系统包括供气管道、活门、终端开关、控制及指示器。
The wing anti-ice system prevents ice buildup on the wing leading edge slats, this system consists of air supply ducts, valves, terminal switches, controls and indications.
应用逆向重构技术，对长耳鸮翼前缘非光滑形态特征几何信息进行量化，并建立仿生类比模型。
Applying the reverse reconstruction technique to quantify the geometry information about the nonsmooth leading edge shape of the long eared owl wing, a bionic analogy air foil model was built.
次要结构由机翼前缘，后缘和翼尖构成，主要用来减小空气阻力，支撑蒙皮，协助飞行操纵面和操纵机构。
The secondary structures, which support aerodynamic fairings or skins, flight control surfaces and control mechanisms, consist of the leading edge, trailing edge, and wingtip.
与今天使用的典型机翼相比，SUGARVolt的机翼的翼尖相距更远，前缘与后缘之间相距更短，并且后掠角更小。
Compared to the typical wing used today, the SUGAR Volt wing is longer from tip to tip, shorter from leading edge to trailing edge, and has less sweep.
使用有限体积法计算了飞行时的气动载荷，分析了前缘切口和翼肋开孔对压强分布的影响；
The finite volume method was used to compute the aerodynamic load, and the effect of leading-edge cut and ribs on the pressure distribution was analyzed simultaneously.
本文介绍了尖前缘翼诱导激波和湍流边界层干扰流场壁面特性，着重强调马赫数影响。
This paper presents the surface characteristics of the inter-action between shock wave and turbulent boundary layer induced by sharp fin with emphasis on Mach number effects.
用速度梯度、压力梯度和环量梯度模拟大攻角尖前缘三角翼流场。
Velocity gradient, pressure gradient and circulation gradient are used to model the separated vortex flow field over a leading edge delta wing.
采用差分方法计算旋涡流场，进而分析三角翼上前缘分离涡的运动特点及其破碎机理。
The vortex flow field is calculated with difference methods, and the motion characteristics and the bursting mechanism of the leading-edge separated vortices of delta wing are analyzed.
本文用正交试验法研究了舵展弦比、前缘后掠角、梢根比和翼剖面对舵性能的影响；
Described in this paper are the effects of the aspect ratio, the swept-back, the taper ratio and the profile of the ship rudder on its hydrodynamic performance by a test method of orthogonality.
本论文主要是通过实验来研究细长圆锥体在大迎角下的绕流流场的特性和细长三角翼加背鳍后对前缘涡的影响，检验相关理论结果。
This paper deals with the numerical solution of the Euler equation for airfoils using approximate boundary conditions and the effects dorsal fin on vortex over delta wing at high angles of attack.
阻力对翼伞升阻比影响很大，前缘切口阻力是总阻力的主要来源之一，且是一种二维效应的阻力。
Drag has a great impact on the lift-drag ratio, and the leading edge cut drag, which has only a two-dimensional effect, is one of the main sources of the total drag.
如此卓著的效率应当归功于低阻机翼、前缘缝翼和双开缝襟翼，以及高马赫混合式翼梢小翼。
This efficiency is due largely to the innovative design of the low-drag wing. This design includes leading-edge slats, double-slotted Fowler flaps, and high-Mach blended winglets.
如此卓著的效率应当归功于低阻机翼、前缘缝翼和双开缝襟翼，以及高马赫混合式翼梢小翼。
This efficiency is due largely to the innovative design of the low-drag wing. This design includes leading-edge slats, double-slotted Fowler flaps, and high-Mach blended winglets.
应用推荐