襟翼

襟翼舵无位置传感器DSP控制系统设计实现

Realization of ship flap rudder control system based on DSP non-position transducer

随后对零航速下襟翼鳍的控制器部分进行了设计，采用模糊自适应PID控制器对其翼型进行控制。

Subsequently , the paper designs the controller of the zero-speed flap fin , using fuzzy adaptive PID controller to control its airfoil .

带有襟翼偏转的三维机翼绕流的N-S方程解

N-S solution of a 3d wing with flap

使用Gurney襟翼降低轴流风扇噪声的简便方法

Simple Method Using Gurney Flap to Reduce Noise of Axial Fan

具有Gurney襟翼的多段翼型空气动力特性分析

The analyses of aerodynamic characters of multi-element airfoil with Gurney flap

Gurney襟翼增升技术在三翼面布局飞机模型上应用的实验研究

Investigation on application of Gurney flap to triplane configuration aircraft lift-enhancement

所采用的建模方法比较完满地解决了K－8机襟翼限位机构（以下简称限位机构）的建模问题，建立了数学模型，以便进行机构的可靠性计算和设计；

The satisfactory mathematical model of K 8 flap spacing mechanism has been set up by the method provided in this paper , so that the reliability of the mechanism can be calculated .

从图中可以明显看出该襟翼鳍在零航速下的减摇效果较好，同时也可以得到模糊自适应PID的减摇效果比传统PID好。

From the simulation results , the anti-rolling effect of the zero-speed flap fin can be seen , and the anti-rolling effect of fuzzy adaptive PID is better than the traditional PID .

Gurney襟翼对单段翼型动态气动特性的影响

Effect of Gurney flaps on aerodynamical characters of single airfoil

超临界翼型Gurney襟翼增升实验研究

Experimental Investigation into Effects of Gurney Flaps on Supercritical Airfoil

三角翼Gurney襟翼增升实验研究

Experimental investigation of Gurney flaps on the lift enhancement of a delta wing

机动襟翼对纵向PIO的影响

Effect of Combat Flap on Longitudinal PIO

Gurney襟翼在某型靶机上的应用

Application of Gurney flap on certain target drone

K8飞机襟翼装配工艺的改进

Improvement of K8 A / C Flap Assembling Technology

Gurney襟翼在风扇叶片上的应用

Application of Gurney Flaps on Fan Blade

用低速风洞测力试验和襟翼处绕流的PIV测量试验研究锯齿形格尼襟翼在不同偏角下的增升效益。

Force and PIV local flow measurements were conducted in a low speed wind tunnel to study the effectiveness of serrated Gurney flap at different deflections .

在一定的条件下，Gurney襟翼可以明显增加翼型的升力系数但不过多增加阻力系数。

Under some condition , Gurney flap can increase lift coefficient and lift drag ratio of the airfoil .

离开飞机时，PIC主要到，双发的整流罩和两侧大翼下部以及发动机附近的襟翼上都糊满了发动机滑油。

On disembarking , the PIC noted the cowls of both engines and the underside of both wings and flaps immediately behind the engines were covered in engine oil .

研究了不同高度的Gurney襟翼在翼型后缘有、无平板（TAB）状态时的增升效果。

In this paper , the results of lift increasement of different highness Gurney flap with and without table ( TAB ) at airfoil trailing edge are investigated .

K-8机襟翼限位机构可靠性建模及求解方法

Establishing and Calculating the Reliability Mathematical Model of K 8 Flap 's Spacing Mechanism

在低速实验中，应用激光片光源和CCD摄像系统，对一装有前端襟翼和前缘襟翼的双襟翼74°后掠三角翼进行实时记录与流态显示的试验技术和图像的三维重建。

A recording system of laser sheet visualization comprising laser source and CCD camera was employed for the visualization and real time recording to investigate the flow past a highly swept delta wing equipped with apex flap and leading edge flaps .

基于Gurney襟翼的低压涡轮叶栅流动控制实验高负荷缝隙弯曲扩压叶栅尾迹特性实验

Experiment on flow control using Gurney-flaps for a low-pressure turbine cascade Experiment on wake characteristics in compound lean compressor cascades with slots injection

以带襟翼舱与不带襟翼舱的GA（W）-1翼型为例，进行了定常流动数值模拟，并与实验结果进行对比分析，验证了多块流场求解程序的可行性；

It has demonstrated that the present method is accuracy and reliability . Through the numerical simulations of steady / unsteady flow for GA ( W ) - 1 airfoil , we have shown that the multi-block solving method is credible .

Gurney襟翼的增升效果不仅与Gurney襟翼的高度密切相关，而且还与在翼面上的安装位置有关。

The increasing lift effect of Gurney flap not only related with highness of flap , but also with the position of flap installation .

采用动量理论结合有限体积法求解N-S方程的方法，进行了螺旋桨滑流对带后缘襟翼机翼气动特性干扰的数值模拟分析。

The N-S equations with adoption of an actuator disk model are used to simulate the effect of turbo-propeller slipstream on high-lift systems . The equations are solved by using the finite volume method .

VY皮瓣推进。倒车舵导管桨后襟翼舵水动力性能计算

Calculations of Hydrodynamic Performance of the Backing Rudder and the Back Flap Rudder of the Nozzle Propeller

K8飞机襟翼装配长期达不到设计要求，成为技术关键。

The assembling of K8 A / C flap can not meet the design requirements in a long time , which becomes a technical key problem .

而与单纯加装Gurney襟翼的模型相比，修改下表面后缘曲率的模型的升阻比可提高14%左右。

Compared with models with simple Gurney flap , the models with the lower surface curvature modified have bigger lift-drag ratio , and it increases approximately by 14 % .

在FL21风洞中进行了高速情况下Gurney襟翼对超临界翼型增升实验研究。

An experimental study was performed on a supercritical airfoil in the FL 21 wind tunnel to investigate the lift enhancement effects of the Gurney flaps at high speed conditions .

Gurney襟翼是指在翼型后缘的下表面垂直弦线、高度很小、厚度也很小的片状增升装置。

Gurney flap is a high lift device , which is a flat with small height and thickness , perpendicular to chordwise of an airfoil , and on trailing edge of lower surface of the airfoil .