With high-speed wind tests of scale models under way, the blended wing could take flight before 2020.
目前，等比例模型的高速风洞测试正在进行中，预计混合机翼能在2020年前起飞。
Vibrating in the wind, the bristles create some drag. But they also reduce the wing's slipstream, an area of low-pressure turbulence that pulls back on the wing, and hence reduce drag.
风中振动时，刷毛会产生反作用力，但同时它也可以减少机翼滑流，产生一个低气压乱流，机翼上形成回力，因而减小阻力。
This illustrates the initial "pop" of the lower wing. the Wind dictates how hard this input is and how fast the next input occurs.
这说明了初始作用在下翼上的弹拉的效果。风力决定了动作的力度和下一个动作的时机。
The viscous flow around M6 wing and F4 wing-body configuration are simulated and compared with the results of wind tunnel experiment.
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。
But the wing also solves a basic problem of sailing: how to take full advantage of the wind without overturning.
翼的存在还解决了航行中的一个基本问题：如何在不倾覆的前提下完全利用风力。
The paper deduces the theoretical derivation of figure coefficient of wind load in wing tunnel test, which can do help data processing of wing tunnel test.
较详细的演绎了风洞测压试验中关于风载体型系数的理论推导公式，为风洞试验数据处理提供了帮助。
The pressure field measurement results on the wing surface of airplane model by luminescence pressure sensor (LPS) technique and classic tap technique in high speed wind tunnel are presented.
介绍了国内首次在高速风洞中使用荧光压力传感器(LPS)技术对飞机模型机翼表面压力场测量的初步结果。
The results of the wind tunnel test show the flutter critical speed of the wing model increases by 37% after the implementation of AFS system.
风洞试验结果说明，采用颤振主动抑制控制系统后，机翼的颤振临界速度可提高37%。
The phenomena "limit cycle" occurred in wind tunnel test for active flutter suppression of a wing model are numerically explained using Harmonic Balance Method.
本文采用谐波平衡法，定量地解释了机翼颤振主动抑制风洞试验中出现的极限环现象。
An experimental study of the effects of the twin vertical fins position and twist strake wing on a fighter aerodynamic characteristics was performed in the wind tunnel.
针对边条弯扭及改变双立尾展向位置对全机纵横向气动特性的影响进行了试验研究。
This paper gives a brief description of the whole process of the low-speed wind tunnel test for active flutter suppression of a two-dimensional wing model with trailing edge control surface.
本文简要地阐述了具有后缘控制面的二元机翼模型主动颤振抑制低速风洞试验的全过程。
The flow field of the wing tip vortex, which shed from a rectangular wing, is surveyed by a seven holes probe in a low speed wind tunnel.
应用七孔探针空间流场定量测试技术研究了翼尖涡的流动结构，给出了翼尖尾涡在下游两倍弦长距离内的速度和压力场分布随迎角变化的规律。
Modal test and parameter identification of a wind tunnel flutter model simulating a wing with external missiles are presented in this paper.
本文介绍了带外挂风洞颤振模型模态试验与参数识别方法。
Modal test and parameter identification of a wind tunnel flutter model, similar to a wing with external missiles, are presented in this paper.
本文介绍了带外挂风洞颤振模型模态试验与参数识别方法。
I now have several wind tunnel pictures of this design, but they have not been scanned in. The second appears to be the one I previously sent, with a fuselage with a cockpit forward of the wing.
我现在有几个风洞的照片，这样的设计，但他们并没有被扫描英寸的第二个似乎是一个我以前发出，与机身与驾驶舱的前进方向，机翼。
The wind of Death's imperishable wing?
以及死而不朽的羽翼所鼓荡的风流？
The effects of Gurney flap on double delta wing aerodynamic performance in low speed wind-tunnel tests;
双三角翼气动布局比三角翼飞机具有更好的大攻角空气动力特性。
This article investigates the flow control technique of forward-swept wing blended body (FBB) tailless configuration by means of wind tunnel tests.
通过风洞试验研究了前掠翼融合体无尾气动布局(FBB布局)的流动控制技术。
The aerodynamic characteristics of the free wing are investigated in this paper. The wind tunnel test results shows that the control of the angle of attack of the fre…
通过风洞试验，对带升降副翼控制的自由翼气动特性也进行了实验研究，验证了位于自由翼后缘的升降副翼可有效地控制自由翼相对气流的平衡迎角。
The effects of flapping frequency, wind velocity, Angle of attack, plane shape of wing and cambered aerofoil are investigated.
试验中进行了扑动频率、风速、迎角、机翼平面形状、翼型弯度对机翼气动特性影响的研究。
The wind tunnel experiments include four aspects:1) A wind tunnel investigation of twin-vertical-tails buffet of a strake-wing layout was conducted to study the test method of tail buffet.
实验研究方面的内容和成果主要有四个方面：（1）边条翼布局飞机模型双垂尾抖振风洞实验研究。
Results of wind tunnel test provide technology support for application of wing with wing-blade in flapping-wing micro air vehicle.
研究结果可为带翼刀机翼在扑翼飞行器上的应用提供技术支持。
The result of wind tunnel test provides guideline in aircraft design of flapping-wing MAV.
本文研究为带翼刀机翼在扑翼飞行器上的应用提供技术支持。
The result of wind tunnel test provides guideline in aircraft design of flapping-wing MAV.
本文研究为带翼刀机翼在扑翼飞行器上的应用提供技术支持。
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